DE102009008912A1 - Propellant gas generating device for generating propellant gas under pressure to perform mechanical operation, has propellant gas pressure vessel for generating propellant gas and combustion chamber with burner - Google Patents

Abstract

The propellant gas generating device (2) has a propellant gas pressure vessel (4) for generating propellant gas and a combustion chamber (6) with a burner (8) for burning fuel for generating combustion gas. The combustion chamber is connected with the propellant gas pressure vessel. Independent claims are also included for the following: (1) a method for generating propellant gas under pressure to perform mechanical operation; (2) an expansion machine for converting energy in propellant gas under pressure; (3) an arrangement for two expansion machines; (4) a method for operating expansion machine; (5) a thermal engine for producing a mechanical movement by a fuel; (6) a method for operating thermal engine; (7) a compressor for compressing a process gas, particularly air; and (8) a steam generator for producing water vapor from water.

Description

The The present invention relates to a propellant gas generating device for generating a propellant gas under pressure to perform mechanical Work and a method for operating such a propellant gas generating device. The present invention further relates to an expansion machine for converting an expansion of propellant gas under pressure into a mechanical one Movement, in particular in a rotary motion, and a method for operating an expansion machine. Furthermore, the invention relates a heat engine for Generating a mechanical motion using a fuel comprising a propellant gas generating device and an expansion machine, and a method of operating a heat engine. Farther the invention relates to a compressor for compressing a process gas, in particular air for use in a propellant gas generating device.

Heat engines are well known. This is basically by burning a Fuel heat and a propellant gas generated at high pressure. This Propellant gas at high pressure is converted into a mechanical movement. The mechanical efficiencies, ie the ratio of mechanical energy, which is contained in the mechanical movement, to the energy, contained by the combustion as heat and pressure in the propellant gas is relatively bad and usually should below 50% or slightly above lie.

The currently highest mechanical efficiencies could of large-volume, slowly rotating two-stroke diesel engines are achieved and in the range of 49%. But even these efficiencies are still low and justified by that much both the thermal energy and the stored in the pressure Energy dissipated due to the operating principle of the machine. Though Nowadays optimizations are performed, but these can nothing to change the basic principle of action and any improvements the efficiencies are limited in their success.

task Thus, the present invention addresses the problems described preferably to fix, or at least reduce. In particular, is the present invention, the object of a heat engine to propose, which in principle allows a better efficiency. At least an alternative machine should be presented.

According to the invention is a Propellant gas generating device proposed according to claim 1.

A such propellant gas generating device comprises a propellant pressure vessel for Generating the propellant gas therein, and a combustion chamber for burning a fuel for generating a fuel gas in which by Combustion heat arises. The fuel gas can then pass from the combustion chamber into the propellant pressure vessel, in addition Secondary fuel, In particular, water is added to absorb heat the fuel gas. As secondary fuel can be liquid water, Steam, compressed air or other suitable gas used become. By feeding of the secondary fuel absorb this heat, which resulted overall in a lowering of the temperature of the resulting Propellant gas leads. This creates a cooling effect by a heat transfer from Fuel gas in the secondary fuel while avoiding energy dissipation. Therefore, the secondary fuel also as a coolant and the described process may be referred to as cooling be, with a cooling in the sense of heat dissipation the system does not take place, but a cooling by mixing. The fuel gas along with the supplied secondary fuel then forms the propellant gas. This propellant gas can then in particular while maintaining a pressure, at least part of its pressure, from the propellant gas generating device for further use, namely conversion in mechanical motion, be forwarded. The propellant gas generating device, in particular the propellant pressure vessel has at least for this purpose a propellant gas outlet.

According to this Arrangement thus becomes the secondary fuel fed directly to the fuel gas and mixed with it. The secondary fuel then forms a component of the propellant gas. When the cooling goes thermal energy from the fuel gas to the secondary fuel over, this transferred to the secondary fuel thermal energy is maintained in the propellant because of the secondary fuel Part of the propellant gas remains.

Preferably the combustion chamber is located in or forms the propellant gas pressure vessel a part of the propellant pressure vessel. Thus, in one case, the combustion chamber may be considered substantially closed Be formed space with corresponding combustion chamber walls, the in the propellant gas pressure vessel is arranged. The chamber outer walls are then in contact with an interior in the propellant pressure vessel. The Combustion chamber then has an opening to the propellant pressure vessel interior so that fuel gas can flow from the combustion chamber into the propellant pressure vessel. The heat of the combustion chamber can also be in the chamber walls in the LPG pressure vessels be radiated.

According to another variant forms the Combustion chamber part of the propellant pressure vessel. In other words, an interior of the combustion chamber is basically flowing into the interior of the propellant pressure vessel over. In particular, for example, the burner can be arranged at one end of a room, and the secondary fuel supply can be arranged at a certain distance from the burner. At an even further distance from the burner then an outlet opening for forwarding the propellant gas is arranged. Thus, in this case, the combustion chamber basically flows into the propellant pressure vessel or its interior.

According to one another embodiment It is suggested that the combustion chamber with burner a fuel supply for feeding of the fuel and an air supply for supplying air. Under Air is in this context in general a substance to understand that together with the fuel after ignition Burning leads or this favors. Air is an easy available to be put variant. Naturally could as well pure oxygen or another suitable gas can be used, which in particular has oxygen. As fuel is preferred a liquid and / or gaseous present fuel such as gas, such as biogas, Natural gas, oil and other oil products such as diesel, gasoline or kerosene, to name just a few examples. Further examples for Fuels are flammable suspensions, emulsions and coal dust.

Of the Burner is according to this embodiment prepared to mix the air and the fuel, in particular to swirl and start a combustion in the combustion chamber to realize. The propellant gas generating device uses this preferably compressed air, thus under pressure with the burner and thus fed to the combustion chamber becomes. For this purpose, a compressor or air compressor is used, which generates and supplies such compressed air. The air compressor may be part of the propellant gas generating device or the compressed air can be provided externally from a compressed air supply. Optionally, an air flow control valve for controlling the pressure and / or for controlling the amount of compressed air provided. This allows the firing process by appropriately controlled addition the compressed air are regulated.

According to one another embodiment a fuel pump and / or a fuel compressor is provided, in particular to fuel the combustion chamber and / or the burner to be supplied under pressure. Preferably, a fuel quantity control valve is provided for Control the supplied Amount of fuel. As a result, in particular, together with the control of the supply of air combustion in the combustion chamber to be controlled. Preferably, the fuel pump and / or the fuel compressor is connected to a fuel pressure accumulator, for a pressure reserve for to produce the fuel.

Preferably is a secondary fuel pump, in particular a water pump provided to the secondary fuel or water at the secondary fuel supply provide under pressure to introduce this under pressure in the LPG pressure vessel. Furthermore, this can be done optionally a water flow control valve may be provided for controlling the supplied Secondary fuel or water quantity. This also makes the production of the propellant gas better controllable, by supplying the Sekundärtreibstoff- In particular, the amount of water is regulated, thereby limiting the process the propellant gas production and / or the composition of the propellant gas to control.

Incidentally, is to note that the burner and thus also the propellant pressure vessel under Atmosphärenüberdruck is working. Accordingly must the to be supplied Media are supplied with at least this pressure.

According to one another embodiment a control unit is provided for controlling the propellant gas generating device, in particular for controlling the fuel supply, the air supply and / or the secondary fuel supply. Such a control unit, which also serves as a measuring, control and regulating unit can be designated evaluates relevant inputs such as operator input and actual values off and on by appropriate controls by preferably corresponding Control commands are given to actuators. Preferred input values are an operator input, especially performance target and various Measured values such as temperature values, for example in the combustion chamber and / or in the pressurized gas container, Pressure values and a connected expansion machine, the Energy in the propellant gas converts into a rotary motion, a speed measurement. The output accordingly form control commands or control signals for one or multiple air flow control valves, one or more fuel quantity control valves and one or more control valves for secondary fuels, in particular Water flow control valves. For a connected expansion machine can also its actuators with control commands or control signals be supplied. For this purpose, a filling valve for supplying the Propellant gas in the expansion machine as well as an outlet valve for Omission of propellant gas from the expander count.

Task of this control unit, in particular Numerical, measuring and control unit is based on a basic program and depending on the variable inputs to calculate the best possible LPG generation and to control them accordingly. In particular, it depends on the volume, pressure, temperature and environmental values.

According to one Another embodiment, a secondary fuel line is provided for conducting the secondary fuel to the secondary fuel feed, the along at least one wall of the propellant pressure vessel extends to a preheating of the secondary fuel by heat the propellant pressure vessel to reach. The feeder of secondary fuel, In particular water, preferably has the purpose that cooling the Fuel gas to a warming of the secondary fuel and in particular to a volume expansion of the secondary fuel leads. As a result, a total of a large volume expansion of the propellant gas sought. It does not necessarily matter that the secondary fuel preferably cold the propellant pressure vessel supplied becomes. As favorable has rather proven to cool the container walls so that they possible take no thermal damage. This can be done by running the secondary fuel through secondary fuel lines along at least one wall of the propellant pressure vessel. The wall of the propellant pressure vessel is thereby cooled and the secondary fuel, especially water, heated. This heated Secondary fuel, especially water, can then in the heated form so in the flow direction the water after the described secondary fuel lines in the LPG pressure vessels introduced become. The temperature here may already be so high lie that the water is already vaporous, so as water vapor supplied becomes. This water can then generate thermal energy from the fuel gas assume and contribute to a volume and / or pressure increase of the propellant gas.

A Another preferred embodiment provides that the LPG pressure vessel at least Sectionally executed at least double-walled and between two walls of the secondary fuel and / or the air for feeding to the compressed gas tank or the combustion chamber out becomes. It should be noted that in the LPG pressure vessel, in particular if the combustion chamber forms part of it, at different Different temperatures can be expected. The highest temperature is functionally in the range of the burner and thus the combustion chamber to be expected and it will decrease to Treibgasauslass out. Consequently can in the combustion chamber, for example, a drewandigkeit be provided. In the area approximately in the middle between burner and LPG outlet can a Doppelwandigkeit and the Treibgasauslass out finally a Einwandigkeit be provided, to name just one example. The Three-walledness can be used to be in an area between two walls Air for feeding to the LPG pressure vessel or to lead to the combustion chamber. In the area of three-walledness may be in another intermediate area and to the two-walled area of the compressed gas tank towards the secondary fuel especially water become. After the place to feed of the secondary fuel can then a Einwandigkeit be provided for Treibgasauslass out.

A another embodiment beats a second secondary fuel supply for feeding another secondary fuel in front. Thus, as a first secondary fuel, for example. Compressed air be provided and as a second secondary fuel water or water vapor. The secondary fuels are for feeding in the propellant pressure vessel intended. And it is important to emphasize that secondary fuels differ are from a combustion air, which burns into the combustion chamber is initiated with the fuel. The secondary fuels are not supposed to participate in the burning, but after that are initiated and an increase in volume of the Reach propellant gas. Basically according to a another embodiment the introduction of even further secondary fuels may be provided.

A another embodiment beats a heat exchanger before heating at least one secondary fuel from heat of the propellant and / or heat another medium. As a result, heating of the first, second and / or further secondary fuel achieved, allowing an introduction of the secondary fuel concerned in the propellant pressure vessel in preheated condition can be done easily. For heating, heat of the propellant may be used by propellant gas to the heat exchanger supplied becomes. The propellant gas can this example. After leaving one of Propellant gas generating device downstream expansion machine be used. It can also be used propellant that the Direct fuel gas generator has left immediately, or one Combination. Furthermore, others are used for use in the heat exchanger heat-conducting media into consideration, such as geothermal gas.

For operating a propellant gas generating device, a method according to claim 11 is proposed according to the invention. This method is thus used to generate a propellant gas under pressure that can be used to perform mechanical work. For this purpose, a propellant gas generating device is used which comprises a propellant pressure vessel, a combustion chamber and a Secondary fuel supply has. The following steps are proposed, which are carried out essentially simultaneously, in particular continuously and thus in parallel. Thus, a fuel is burned in the combustion chamber to generate a fuel gas. This fuel gas has a high heat, as well as a certain overpressure, which is also due to the construction of a closed combustion chamber. In this case, an open combustion chamber is also to be understood as an open combustion chamber arranged in a substantially closed propellant pressure vessel. The fuel gas is directed into the LPG pressure vessel. This is done for example by a discharge of a generated propellant gas and the continued operation of the burner, so that fuel gas complies. Secondary fuel, in particular water, is introduced into the propellant pressure vessel and thus into the fuel gas. This leads to the cooling of the fuel gas and thereby to a heating of the secondary fuel, in particular of the water, and a consequent expansion of the secondary fuel or water. As a result, the propellant gas is generated in the propellant gas pressure vessel, which has a correspondingly high pressure and can lead to a corresponding increase in volume of the propellant gas. According to one possibility, the secondary fuel is atomized and / or introduced as water vapor. As far as possible, the introduction is carried out so that the most favorable possible mixing of fuel gas and secondary fuel to the propellant takes place. Incidentally, the secondary fuel is supplied under pressure.

Preferably In this method, a propellant gas generating device according to the invention used, as already explained above.

Cheap is Thus, as has already been partially explained, when burning of the fuel to the fuel gas with the supply of air, as secondary fuel Water in liquid Form so fed that will do it when cooling evaporates the fuel gas and thus leads to an increase in volume or already supplied as water vapor is and / or the propellant fuel gas and water vapor, in particular a mixture of fuel gas and water vapor. The burning of the Fuel is supplied by the feeding of air, which also exemplifies other additives such as Oxygen is favored and in particular better controllable.

Preferably the propellant gas is generated so that the combustion under pressure takes place. This is a characteristic of the burner and makes appropriate precautions needed in particular the fuel and, if necessary, to supply the air under pressure. Corresponding is too - like already explained above was - the secondary fuel the compressed gas tank to be supplied under pressure.

According to others embodiments it is proposed that the combustion chamber is supplied with compressed air, which is provided by a pneumatic compressor, preferably a compressed air control valve is used and the pressure and / or the Amount of compressed air is controlled. It is also favorable, the combustion chamber and / or the burner fuel by means of a fuel pump and / or a Supply fuel compressor, wherein preferably a fuel quantity control valve is used and wherein the supplied Fuel quantity is controlled. When using a gaseous fuel is for the control of the fuel quantity valve monitoring the pressure, the temperature and / or the volume and / or mass flow of the supplied fuel proposed. In addition, the propellant pressure vessel is preferably water as the secondary fuel supplied by means of a water pump and optionally a water control valve that uses water under pressure supplied and the supplied Controlled amount of water. Likewise, if necessary, the controller the pressure and / or the amount of water are performed directly on the water pump. The feeder of a gaseous secondary fuel can be similar to the feeder a gaseous one Fuel or the compressed air are made.

Preferably you will the process as a flowable fuel, so one liquid or gaseous Fuel, in particular gas, oil, gasoline and diesel, to only to give some examples.

As even in connection with the propellant gas generating device explained was, can according to one embodiment preheated water as secondary fuel be used and / or pressurized water in the propellant pressure vessel be fogged. This makes it possible for the water before Cool the propellant pressure vessel or other components of the propellant gas generating device or other components of a heat engine to use. The to preheat extracted heat remains in the system by supplying the thus preheated water obtained to the fuel.

Preferably, the method is carried out such that the water or secondary fuel supply, the fuel supply and / or the compressed air supply is dependent on measurements of conditions in the propellant gas generating device, in particular depending on measurements of the temperature, the volume, the pressure and / or the composition of the Propellant gas and / or depending on the temperature in the burner takes place. Preferably, a control of the proportions and / or the Pressure of compressed air, fuel and water carried out.

According to one embodiment It is proposed that the method be controlled so that the Propellant the propellant pressure vessel for example with a pressure of 10 to 50 bar and a temperature in the range from 750 ° C up to 1200 ° C leaves. The temperature is higher, The higher the pressure is and vice versa.

In addition, according to the invention an expansion machine according to claim 22 proposed. Such an expansion machine has a filling space and a propellant expansion space. It is in the filling of the moving body arranged and guided, that a pressure of the propellant gas, with which the filling space has been filled, acts on the first pressure surface and the moving body pushing and moving in a first direction. This movement may result from an expansion of the filled propellant gas or in combination it along with the filling respectively. In other words, by filling with propellant gas of the moving body immediately be moved in the first direction. The moving body is also guided into the Treibgasexpansionsraum, the second pressure surface basically the first printing surface is opposite and an expansion of the propellant gas expansion space supplied propellant gas to a movement of the moving body moved in the second direction opposite to the first direction becomes. The expansion machine is essentially prepared to that a movement of the moving body in the second direction due to expansion of the propellant gas in the propellant gas expansion space he follows. The effect of the propellant gas in the filling space and the propellant gas expansion space are thus contrary. In particular, the expansion machine is special accordingly to control so that a filling of the filling space and an expansion the propellant gas in the expansion space successively, in particular takes place alternately.

Preferably is the first printing surface smaller than the second pressure surface. In the filling room becomes a higher one Pressure needed, to apply the same force to the moving body as in the propellant gas expansion space be exercised by a correspondingly lower propellant gas pressure can. Here are the forces in the direction of the first or second movement direction.

A embodiment beats before that the filling space is designed as a cylinder space or annular gap and accordingly the first printing surface as circle or ring surface is formed, the moving body designed as a piston is and / or the propellant gas expansion space as an annular gap or cylinder space is formed and formed the second pressure surface as a ring or circular surface is. The use of a piston as a moving body is structurally simple to design. The first expansion part assembly can thereby total be simple and essentially cylindrical. For example the filling room an annular gap and the first pressure surface corresponding to an annular surface and the Treibgasexpansionsraum a cylinder chamber with the second pressure surface as Circular area. In this way it is also easy to realize that the first printing surface smaller than the second pressure surface is. Likewise, the division may be reversed, a larger ring area than the circular area is with appropriate size distribution to reach.

According to one Embodiment overlap the filling room and the propellant gas expansion space, both preferably in one common bore are formed. Accordingly, a common Bore be provided as a common cylinder chamber, in the the movement body especially as a piston can move and the filling space is then on one side formed of the piston and the Treibgasexpansionsraum at the other Page. Parts of the hole belong then depending on the piston position to the filling space or propellant gas expansion space.

Preferably The expansion machine includes at least one functional with the first filling space connected filling valve for admitting propellant in the first filling space, at least one with the Propellant expansion chamber functionally connected exhaust valve to Omitting propellant gases from the propellant gas expansion space and / or at least one with the filling room and the Treibgasexpansionsraum functionally connected overflow valve for opening and Shut down a connection between the filling space and the propellant gas expansion space to allow propellant gas from the filling room to Propellant gas expansion space to flow. The filling room and the propellant gas expansion space are thus functional over the at least one overflow valve connected. Overall, this expansion sub-assembly is thus prepared to that a propellant gas over the filling valve in the filling room flows, there to a movement of the moving body in the first direction leads, then via the overflow valve flows into the Treibgasexpansionsraum, there expands and closed a movement of the movement piston leads in the second direction and subsequently - preferably after complete Expansion and pressure decrease to atmospheric pressure - the propellant gas expansion space leaves.

According to the invention, an expansion machine according to claim 27 is also proposed. This expansion machine has an expansion part assembly with a double function, the ins special is tuned to cooperate with a propellant gas generating device. Accordingly, a propellant gas expansion space is provided, which is to be filled with propellant gas and in which the propellant gas is then expanded to push the moving body in a first direction and to cause a corresponding translational movement of the moving body in this first direction. This moving body is also guided in a compression space and has a compression surface to compress a process gas, in particular air, which may be used in the propellant gas generating device, to compress. Compression is effected by a translational movement of the moving body in the first direction, so that a movement of the moving body caused by the expansion of the propellant gas leads to a compression of the process gas into the compression space.

Preferably is the printing surface bigger than that Compression surface. This can be achieved on the one hand, that the same expansion pressure on the printing surface to a compression with higher compression pressure on the side of the compression surface to lead can. On the other hand it is achieved that the expansion of the propellant gas a movement of the moving body can reach in the first direction with high energy or force and the done with it Compression of the process gas from this energy or force only a little consumed.

there is preferably a common cylinder space or a common one Bore provided in which the propellant gas expansion space and the compression space are formed. Basically, during movement, the moving body then moves - in particular as a piston - between the propellant gas expansion space and the compression space back and forth.

Cheap is it, at least one of the expander subassemblies a jacket tube to provide a medium for temperature compensation therein. hereby can be a temperature compensation between different warm areas the expansion part assembly can be achieved. The medium used is thermal oils, water, Gases and other media into consideration. A temperature compensation can also in the area of cylinder heads be provided and the medium used for heating be used elsewhere.

According to one preferred embodiment two expansion sub-assemblies, ie a first and a second coupled together. This coupling can be both with an expansion subassembly with filling space and propellant expansion space as well as with an expansion subassembly be made with compression space and Treibzasxpansionsraum. The two expansion sub-assemblies are therefore basically in push-pull coupled, so that an expansion of propellant gas in the propellant gas expansion space expand the first expansion part assembly to a drain of the Propellant gas from the Treibgasexpansionsraum the second expansion sub-assembly leads. The function of the filling spaces or the compression rooms remains accordingly preserved as they are already related has been explained with a single expansion part arrangement.

at Use of two compression chamber expansion subassemblies Thus, an alternating expansion of propellant gas in the respective Propellant gas expansion space performed, which leads to a translatory movement, which in a rotational is converted, while at the same time also mutually process gas compressed and as a compressed process gas, in particular as compressed air is ready and supplied to the propellant gas generating device can.

Preferably a flywheel is provided for storing and dispensing a Kinetic energy from or to the moving body. Such a flywheel can absorb kinetic energy, especially if the respective Propellant expansion space, which is just expanding in the propellant gas, still small and the pressure of the propellant gas is still high. An increasing Expansion of the propellant gas and thus an increase of the propellant gas expansion space leads as well to a decrease in pressure of the propellant gas and according to a power decrease of the moving body. Towards the end of the movement, this movement can be sustained by the flywheel even if a subsequent device is mechanical energy extracts. This makes it at least theoretically possible that the pressure of the propellant gas decreases towards the end of the movement to atmospheric pressure. This would be avoided, propellant gas with overpressure to let escape at the end of the movement and thus give away energy. It should be noted that although towards the end of the movement the flywheel takes over part of the movement, the - though weak - expansion power or Pressure force of the propellant gas nevertheless makes a contribution to the movement.

According to a further embodiment, a conversion mechanism is proposed which has at least one connected to the moving body rack and at least one coupled to the rack gear means for converting a translational movement of the rack in a rotatory cal movement on the gear means. This device has the advantage over a construction of wheel and connecting rod, that of the rack basically always the same force in the same torque is achieved because the use of the rack on the gear means permanently force application is achieved at a 90-degree angle from the translational direction of movement to the radius at which the rack engages.

Preferably the expansion machine is characterized in that the conversion mechanism at least a first gear means to a translational Movement of a first direction of the moving body in a rotational movement with to convert a first direction of rotation and a second gear means has a translatory movement of a second direction of the moving body to convert into a rotational movement with the first direction of rotation. It So in any case, a translational movement into a rotary motion converted with one and the same direction of rotation. It is suggested that switches between the first and second gear means so is that a movement of the moving body in a rotary motion with the first, so only one, direction of rotation is changed. Preferably has each gear means for this purpose a freewheel, in particular a controlled clutch freewheel to each only at the first or the second direction of the translational movement is effective to be. Accordingly, according to a variant, no active switching is required carried out and there will always be a transformation in the first mentioned Rotational movement performed. If a controlled clutch freewheel is used, it is possible to use the Free-wheeling deliberately to deactivate, so that a force from the gear means also transferred to the moving body in the aforementioned direction of rotation can be. This can be advantageous if to an end position of the moving body Its movement through the gear means are still supported should.

Preferably can the moving body with two racks or a double rack to be formed by a rack or a part of a double rack for each a translatory movement leads to a transmission.

The Expansion machine control unit is according to one embodiment prepared to the movement of a linear unit, in particular Piston and piston rod includes to control via valve positions. Furthermore can if necessary, clutch freewheels be controlled to suitably control a torque transmission. In particular, the measurement and consideration of the state variables piston location, Piston speed, piston movement direction, generated speed provided on an output shaft and valve positions and possibly states of the clutch freewheels. When coupling several expansion machines, the expansion machine control unit Be prepared to use these expansion machines in their movement to coordinate. Preferably, a central control unit may be provided which, in addition to the tasks of the expansion machine control unit the control of a propellant gas generating unit preferably takes over can be a control unit for a propellant gas generating unit and an expansion machine control unit coordinated and / or combined in one unit.

In addition, according to the invention proposed an arrangement of at least two expansion machines, wherein the expansion machines are coupled to each other direct a torque to a common shaft, in particular the Expansion machines are prepared, synchronized and / or to be coordinated. Here, two expansion machines on a Conversion mechanics be coupled by, for example, each expansion machine with a rack on a conversion mechanism with two gear means attacks. Likewise two, or more expansion machines a torque on one transmit common wave, wherein the expansion machines individually or in pairs in the axial Direction of the common shaft are arranged one behind the other. In any case when coupling several expansion machines of the same design and size and / or Using the same conversion mechanisms, the expansion machines in the Synchronous be coupled. They run at least partially phase-shifted, but otherwise synchronous, or with the same frequency.

In addition, according to the invention a method for operating an expansion machine with a first Expansion part assembly with a filling space and a propellant gas expansion space according to claim 35 proposed. Accordingly, the following steps are performed: Im First step will be the filling space over at least a Füllraumbetreibgas filled, wherein the pressure of the propellant acts on a first pressure surface on the moving body and push it in a first direction and thus in that direction emotional. In the second step, the at least one filling valve closed and then at least one overflow valve open, so that the propellant gas from the filling space flows into a propellant gas expansion space. The opening of the at least one overflow valve can over the closing the at least one filling valve a little later, so later, done to a stream of propellant gas directly into the filling valve, and through the overflow valve, to prevent. In the propellant gas expansion space, a force acts the second printing surface the moving body and this is pressed with it in a second direction and moved with it. The second direction is opposite to the first, so that the movement body opposite step 1 moved back again.

in the third step is at least one exhaust valve in the propellant gas expansion chamber open, to allow the propellant to escape from the propellant gas expansion space. The pressure of the propellant gas is optimally equal to the surrounding, So atmospheric pressure.

in the fourth step, the procedure is repeated beginning with step 1, wherein the at least one outlet valve initially remains open. In the movement of the moving body in the first direction according to step 1, the Treibzasxpansionsraum is again reduced and by the at least one opened Exhaust valve can escape the contained propellant gas.

According to the invention is also a Method for operating an expansion machine with an expansion subassembly with a propellant gas expansion space and a compression space according to claim 36 proposed. Accordingly, in the first step, the propellant gas expansion space filled with propellant, so that the pressure of the propellant gas on a pressure surface at one moving body acts and the movement body thereby moved in a first direction. Through this movement in the first direction, the compression space is reduced and that in it contained compressed process gas. The compressed process gas can following or already during compressing its use.

in the second step, the moving body in the second direction moved back, wherein the propellant gas expansion space due to at least one open Outlet valve is emptied. The return movement of the moving body can for example, by a flywheel or another not through achieved this first expansion part assembly caused force become. In this second step, the compression space with Process gas filled. In the simplest case, this can mean that an inlet valve is in the compression space is opened and by moving back of the moving body Air flows into the compression space.

in the third step, step 1 is repeated, but before anyway closed the described intake valve in the compression space became, so that a desired Compression pressure for the Can build process gas.

Preferably two expansion sub-assemblies are coupled with the same features operated. The same characteristics do not necessarily mean that that the expansion subassemblies are completely identical, but that they have in principle the same structure, in particular two expansion sub-assemblies each with a filling space and are each operated coupled to a propellant gas expansion space, or two expansion subassemblies each having a propellant gas expansion space and a compression space are operated together.

The Movement directions are set against this, with the movements complement each other, in that the two expansion part arrangements have a common moving body. The two expansion sub-assemblies who operated accordingly so that they each the movement body moving in the same direction, so that the filling and emptying of the propellant gas expansion space the first expansion part assembly always reversed for filling and Draining the Treibgasexpansionsraumes the second expansion sub-assembly he follows.

In addition, according to the invention a heat engine for generating a mechanical movement using a Proposed fuel, which is a propellant gas generating device according to the invention for generating a propellant gas and an expansion machine according to the invention for converting an expansion of propellant gas under pressure into a mechanical one Movement, in particular rotational movement, wherein the propellant gas generating device and the expansion machine are coupled together so that the Propellant gas generated by the propellant gas generating device of the expansion machine supplied is, in particular at least one filling valve or inlet valve is provided in a propellant gas expansion chamber. Preferably Here are the propellant gas generators and the expansion machine coordinated. In particular, the propellant gas generator provides essentially a propellant gas with as constant as possible values constant pressure and temperature. The expansion machine is to prepared, essentially with a propellant gas at constant pressure to be operated. The two facilities complement each other thus advantageous to the heat engine. According to one embodiment becomes an expansion engine with at least one expansion space, preferably two expansion spaces used. Thus, the expansion machine with that of the propellant gas generating device provided propellant gas and at the same time Compress process gas and as compressed gas, in particular Compressed air of the propellant gas generating device, in particular the burner be available. This results in particularly good synergy effects.

moreover is a method of operating a heat engine according to claim 40 proposed.

Further according to the invention is a Compres sor for compressing a process gas, in particular air, proposed according to claim 41. Such a compressor has a first and a second compression space, each having a first and second compression body. In this case, a coupling of the two compression spaces takes place in that the second compression space is formed in the first compression body.

Preferably the first compression chamber is prepared for this, the process gas in a first compression stage to a volume with a first one Compression compression. To the compressed process gas then to transfer to the second compression space is a corresponding connection valve - or more - provided. To Compressing in the first compression stage thus flows the process gas in the second compression chamber.

Of the second compression space is then prepared for the process gas continue to compress in a second compression stage, wherein accordingly, the volume decreases and the compression pressure is increased.

According to one Particularly preferred embodiment are the first compression space and the second compression body fixed to each other and the first compression body to the first compression space and the second compression body so arranged in two directions that move his movement either the first compression space reduced or the second enlarged or vice versa. Preferably, the first compression space forms a Cylinder, in which the first compression body is also guided cylindrically. In the first compression body is the second compression space also as a cylinder - accordingly with a smaller diameter - arranged. The second compression body is finally in this second compression space also as appropriate Cylinder with a smaller diameter out. For compressing the process gas this will be done first let into the first compression space, which expands in this case is. The first compression body moves now - after the corresponding valves were closed - so in the first compression space, that this is reduced and the process gas is compressed. There the first compression space and the second compression body, respectively to be fixed, to increase automatically the second compression space by the movement of the first Compression body. Due to the smaller cylinder diameter, this second compression space but relatively small and it can now compress the one in the first compression stage Process gas can be admitted in this second compression chamber, without that this loses its compression again. It can be due to of the small second compression space the connecting valve between the first and second compression space during the first compression stage open be. In this first compression stage, although the second compression chamber enlarged during the first is reduced, it is still compared to the large compression space small and the available Volume for the process gas is also opened Connection valve reduced. For however, the second compression stage must close the connection valve be so when weighing the first compression body, whereby the second compression space is reduced, the process gas not back flows into the first compression space.

Preferably can the connecting valve as a check valve be provided that only a flow from the first to the second Compression space allows. Likewise, an inlet valve from the outside to the first compression space as a check valve be educated.

In addition, will preferably proposed feeders, Lines and possible all elements of a warming are exposed to thermal insulation, in particular heat dissipation too avoid. This is to prevent heat from being used up the system leaves.

A another embodiment beats before, a compressor, so in particular a compressor described, the principle structurally independent from an expansion machine is mechanical with an expansion machine to couple a force generated by the expander to the Operating the compressor to use. In particular, it is proposed to set up such a compressor on a conversion mechanism, in particular to connect with a gear means of the conversion mechanism, so as to operate the compressor.

• – einen Vorwärmbereich zum Vorwärmen des Wassers,
• – einen Verdampfungsbereich zum Verdampfen des Wassers und
• – eine Wärmequelle zum Erwärmen des Vorwärmbereichs und des Verdampfungsbereichs,

wobei der Dampferzeuger dazu vorbereitet ist, vorgewärmtes Wasser aus dem Vorwärmbereich über Treibmitteleinspritzdüsen in den Verdampfungsbereich einzuspritzen, sodass das Wasser in dem Verdampfungsbereich zu Wasserdampf verdampft, wobei die Wärmequelle vorzugsweise dazu vorbereitet ist, ein Heizmedium bereitzustellen und/oder zu erzeugen, das zunächst zum Verdampfungsbereich geleitet wird um diesen zu erwärmen und von dort zum Vorwärmbereich geleitet wird um diesen zu erwärmen.According to the invention, a steam generator is also proposed for generating water vapor from water comprising:

• A preheating area for preheating the water,
• - An evaporation area for evaporation of water and
• A heat source for heating the preheat area and the evaporation area,

wherein the steam generator is prepared to inject preheated water from the preheat region via propellant injection nozzles into the evaporation region so that the water in the evaporation region evaporates to water vapor, the heat source preferably being prepared therefor is to provide and / or produce a heating medium, which is first passed to the evaporation area to heat it and is passed from there to the preheating area to heat it.

Cheap is it is to use such a steam generator as a heat exchanger, in particular to propellant gas of a propellant gas generating device as a heat source after it has gone through an expansion machine and thereby in the heat exchanger To generate water vapor for use as secondary fuel in the propellant gas production facility.

To explain some terms:

Of the first expansion space can also be referred to as Treibgasfüllraum and the second expansion space may also be referred to as propellant gas expansion space become.

fuel and / or fuel may also be referred to as fuel, differs in its function from the secondary fuel. Fuel, Fuel and fuel are in the importance of secondary fuel delineate.

Propellant pressure vessel can also as Treibgasreaktordruckbehälter be designated.

A Control unit usually includes a Measuring and control unit.

It It should be noted that a printing surface is a part of a total area can form, but the pressure on the total area, but only on the printing surface is effective. The term pressure surface refers to the area at which the pressure becomes effective.

In addition, according to the invention an expansion machine according to claim 34 proposed. Further preferred embodiments will be apparent the dependent claims.

Prefers a conversion mechanism has a flywheel for storing Rotational energy on. Such a flywheel is preferred as Rotor of a generator, in particular an electrical synchronous generator or asynchronous generator formed. The rotor will be corresponding rotatably disposed in a stator to relatively by its Drehwegung to generate electricity to the stator, in particular in the stator. Likewise comes an outside lying rotor or an outer rotor design in Consideration. In certain circumstances can the execution with outside rotor lying a larger rotor diameter and a higher one moment of inertia exhibit. The storage of an increased amount of rotational energy would be sometimes possible.

The rotor and thus the generator as a whole can be arranged directly in the conversion mechanism or arranged at an at least somewhat remote position and connected via a corresponding shaft with the conversion mechanism. Does the conversion mechanism a plurality of axes of rotation and thus waves, z. B. two sprockets and thus two waves according to the in 14 In the embodiment shown, at least one rotor can be provided as a flywheel and, correspondingly, a generator for each shaft.

By the embodiment of at least one flywheel as a rotor Generator can reduce the effect of the flywheel with the effect of the rotor a generator advantageously combined and combined.

following the invention will be described with reference to some examples with reference to the accompanying figures closer explained.

1 shows a propellant gas generating device with two LPG pressure vessels according to an embodiment of the invention.

2 shows an expansion machine according to an embodiment of the invention in an operating position.

3 to 5 show an expansion machine according to 2 in other operating positions.

6A shows a propellant gas generating device according to 1 , and an expansion machine according to the 2 to 5 that are coupled.

6B shows a heat engine according to 6A , but with a changed operating position of the expansion machine.

7 shows a propellant gas reactor according to another embodiment of the invention.

8th shows a propellant gas reactor according to another embodiment of the invention.

9 illustrates the construction and operation of an expansion machine according to another embodiment of the invention.

10 to 12 show a heat engine according to an embodiment with two propellant gas reactors and an expansion machine in a schematic representation and in different operating conditions.

13 shows a heat engine with Propellant gas reactors and an expansion machine, which is connected via its conversion mechanism with a compressor according to an embodiment.

14 shows a conversion mechanism which is coupled with two toothed piston rods in a perspective view.

15 schematically illustrates the force and torque effects of in 14 shown arrangement.

16 shows a further embodiment of a heat engine schematically.

17 shows a section of an expansion machine according to another embodiment.

18 shows a piston of an expansion machine according to another embodiment.

19 shows a cross section through an insulated cylinder of an expansion machine to illustrate the structure.

20 shows a steam generator for generating water vapor from water according to the present invention.

21 shows a further embodiment of an expansion machine in a side view.

22 shows an expansion machine according to the 21 in a top view.

23 shows an expansion machine similar to the 9 , wherein in each case instead of a compression space, a pressure space for filling with propellant gas is used.

24 shows an expansion machine similar to the 23 , wherein the pressure chambers are optionally used for compressing a process gas, in particular air or for filling with propellant gas.

One Aspect of the invention is the propellant gas generating device. Basically suitable propellant gas generation can be accomplished in a variety of ways. According to the selected energy source (fuel) the appropriate technology should be chosen. For solid fuels like Coal, wood, etc. come z. B. commercial steam boiler systems in Question. In liquid Fuels like oil, or gaseous Fuels such as landfill gas, biogas, natural gas, etc., can the propellant gas generating device according to the invention be used.

• 1. Die Energieumwandlung vom Energieträger zum Treibgas sollte einen Wirkungsgrad μ > 90% haben.
• 2. Die Temperatur des Treibgases sollte zumindest so regelbar sein, dass sie in der Expansionsmaschine keine thermischen Schäden verursacht.
• 3. Der Druck des Treibgases soll regelbar sein.
• 4. Die Volumenmenge des Treibgases soll regelbar sein.

The following properties of the propellant gas generating device are aimed at:

• 1. The energy conversion from the energy source to the propellant gas should have an efficiency μ> 90%.
• 2. The temperature of the propellant gas should be at least controllable so that it causes no thermal damage in the expansion machine.
• 3. The pressure of the propellant gas should be adjustable.
• 4. The volume of the propellant gas should be adjustable.

The propellant gas generating device 2 according to the 1 has two propellant pressure vessels 4 on, which are basically the same structure and incidentally can also be referred to as Treibgasreaktordruckbehälter. The task of propellant pressure vessels 4 it is to produce propellant gas suitable by the reaction of air, fuel and preheated water, so that it is able to perform mechanical work.

Im in each of the two LPG pressure vessels 4 is a combustion chamber 6 with one burner each 8th arranged to burn fuel. Task of the combustion chamber 6 is to ensure the best possible combustion of a fuel-air mixture. The LPG pressure vessel with the combustion chamber 6 forms a propellant gas reactor 5 ,

Every burner 8th is designed to start and ensure optimal combustion by turbulence of air, fuel and their ignition.

Furthermore, the propellant gas generating device comprises 2 a central measuring and control unit 10 , also short as MSRe or MSR 10 designated. Variable inputs of this MSR 10 are an input for a performance target 12 , via which a user can specify a power via operator commands, and at least one input for a temperature measurement 14 , an input for a pressure reading 16 and an input for a speed reading of a mechanism driven by the propellant gas generator. The measured values of temperature and pressure relate to the temperature and the pressure of the propellant, in particular at an outlet 18 the propellant pressure vessel 4 ,

As outputs are the MSR 10 Control commands off. These include an air control output 20 for outputting a drive command to at least one air pressure control valve 22 to supply air to the burner 8th to control a fuel control output 24 for outputting a drive command to at least one fuel control valve 26 to control a fuel supply and a water control output 28 to spend a session order at least one water quantity control valve 30 to control the supply of a quantity of water to the LPG pressure vessel.

Furthermore, the MSR 10 a quantity control output 32 on, for outputting a drive command to control a charge amount of the propellant gas for a downstream expansion engine, and a charge control output 34 for outputting a drive command to control, for a downstream expansion engine, an exhaust valve for discharging the propellant gas from the expansion engine.

The MSR 10 It is intended to calculate, based on a program and depending on the above-mentioned inputs, the best possible propellant gas production and to control it by appropriate control commands.

Furthermore, an air compressor 36 provided by means of a memory in front of the air pressure control valve 22 provides at least one air pressure in one embodiment 43 bar is. The compressor 36 is driven by a linear linkage from the expander to ensure proportional airflow generation.

The compressor 36 Provides compressed air and task the air pressure control valve 22 is it, according to a specification by the central MSR 10 the combustion chambers 6 the propellant gas reactors 5 to supply an optimal amount of air.

A fuel pump 38 is provided to by means of a memory in front of the fuel control valve 26 to ensure a fuel pressure. This fuel pressure is about 200 bar in the present embodiment when using a liquid fuel. The fuel control valve 26 , which is also referred to as a fuel quantity control valve, according to the above-described specifications of the MSR 10 the combustion chambers 6 the propellant gas reactors 5 supply the best possible fuel quantities. For this purpose, the combustion chambers 6 at least one injection nozzle 40 on.

By means of a water pump 42 and a memory should before the water flow control valve 30 a water pressure can be provided, which can be about 200 bar. The water flow control valve 30 should provide for a regulated supply of water to the LPG pressure vessels. This supply takes place according to a specification of the MSR 10 , where the water misting nozzles 44 in the propellant pressure vessels 4 the propellant gas reactors 5 is supplied, each in the range of a container wall 46 are arranged. In this case, optimal amounts of water preheated water to be supplied in order to achieve a temperature and volume optimization of the propellant gas. For the supply of water are from the water flow control valve 30 to the nebulizer corresponding water supply lines 48 intended.

The propellant gas reactor 5 works with a non-atmospheric combustion technique, that is, the combustion takes place under overpressure. It is in the propellant gas reactor 5 Propellant generated from fuel, air and water.

The special task of the propellant gas reactor 5 is to generate propellant gas with the largest possible volume and moderate temperature. By moderate temperature is meant a temperature range that does not damage the engine designs of the propellant reactor pressure vessel 6 and causing an expansion machine to which the generated propellant gas is supplied.

Controlled and controlled by the MSR 10 is via the air compressor 36 , which can also be referred to as a compressed air generator, and the air flow control valve 22 , as well as one the air ducts 35 Comprehensive piping compressed air to a burner 8th comprehensive burner system within the combustion chamber 6 in the propellant reactor pressure vessel 4 fed.

At the same time - also from the MSR 10 controlled - fuel, via the fuel pump 38 with fuel pressure accumulator and the fuel quantity control valve 26 , As well as an associated and fuel lines comprehensive line system the burner system within the combustion chamber 6 in the propellant reactor pressure vessel 4 guided.

Arrived in the burner system are the - maximally optimally composite components - fuel, such as gas, oil, etc., and compressed air intimately mixed and there brought to the ignition, with a significant increase in volume and temperature increase over the burner system in the combustion chamber 6 takes place.

Task of the combustion chamber 6 it is the combustion process to provide a sufficient shelter in which the combustion as optimally as possible, that is, at the highest possible temperatures and the necessary residence time, can take place as completely as possible in order to create the cleanest possible fuel gas. Positive features here are that an optimally optimized combustion time window can be achieved and possibilities for optimal fuel combustion are created, in order to minimize any particulate matter risk and to obtain as little NO _x as possible.

Through in the combustion chamber 6 constructive before seen openings 7 A very hot or hot fuel gas leaves the combustion chamber 6 and enters the larger propellant gas reactor pressure vessel 4 ,

In the propellant pressure vessel 4 is arrived in the very warm fuel gas, also very warm preheated water at high pressure misted.

This process is also controlled and controlled by the MSR, the pressurized water being the water pump before 42 , the water storage and the water flow control valve 30 has gone through. For heating, the water may have a heat exchanger of the compressed air generator or air compressor 36 go through it, whereby it heats up strongly.

Due to the high pressure, in the very warm fuel gas, misted very warm water, both components mix, to one also from the MSR 10 controlled propellant gas.

The MSR 10 System measures, controls and controls the previously described supply of fuel gas and water so that the largest possible propellant gas volume is formed in a temperature range, which the propellant reactor pressure vessel 4 and a downstream expansion machine not damaged thermally.

hereby are no energy outflows outward by cooling necessary, because the too high temperature ranges converted into usable propellant gas volume were. Furthermore, depending on the selected temperature range with low thermal energy flows to count in the propellant gases behind the expander machine, because - according to one Embodiment - this Temperature is only in the range of about 100 ° C.

The task of the LPG reactor pressure vessel 4 is to bundle the propellant gases formed in it and, if necessary, to supply the downstream expansion machine via a pipeline system, and to withstand the expected pressure resulting from the dynamic pressure of the expansion machine.

A Another task of the MSRe system is during the operation of the WWKM constantly the proportions of compressed air, fuel and water as a function of pressure, volume and temperature of the propellant gas to measure and regulate.

A particular advantage of the propellant gas reactor system, ie the propellant gas reactor 5 with associated components including the MSR 10 , is that due to the system takes place a direct intimate temperature-volume conversion. That is, by mixing, a volume increase is achieved directly in the same room. Efficiency losses due to temperature - volume separating solid walls such. B. Pipelines in boiler plants are not available.

When Another advantage is to be expected that any existing in the fuel gas Pollutants are intimately mixed in the propellant gas and after condensation behind the expansion machine are bound in the condensate and thus environmentally friendly treated or disposed of.

It should be noted that the 1 a schematic representation is the two propellant gas reactors 5 in an ajar view of a sectional view in the basic structure shows that does not represent exact proportions. For a better overview are the MSR 10 and further elements between the two propellant gas reactors 5 shown. However, this is not what matters and, in particular, the MSR 10 can be arranged at basically any position.

According to 2 becomes an expansion machine 202 according to an embodiment of the invention, wherein the expansion machine 202 to explain the individual elements in an operating position is shown. For the representation a partial sectional view was chosen.

The expansion machine 202 has two cylinders 204 on - according to 2 a right cylinder and a left cylinder - in which propellant gas can expand at the appropriate operating position. Each cylinder has a cylinder head 206 with several exhaust valves 208 on, can flow through the propellant in the open state. The exhaust valves 208 at the right cylinder 204 are shown in the open and in the left cylinder in the closed state.

For filling each cylinder 204 with propellant gas is ever a ring channel 210 with filling valves 212 intended. At the right cylinder 204 is a closed and the left cylinder 204 an open filling valve 212 shown. In the position on the right cylinder 204 can thus propellant gas on the annular channel 210 be provided and by the at least one, shown on the right filling valve 212 in the cylinder 204 stream.

In every cylinder 204 becomes a piston 214 by means of an annular cylinder guide 216 guided in a cylindrical interior or a cylindrical bore to an axial movement of the piston 214 to enable. The cylinder guide 216 is in and on the cylinder 204 arranged and also ensures a seal of the piston 214 against the cylinder 204 , At every piston 214 is also an annular piston seal 218 arranged the piston also against the cylinder 204 seals and reaches a leadership. The piston 214 has a piston body 220 and a piston end wall 222 which are each firmly connected to each other, said connection of the piston body 220 with the piston end wall 222 in the 2 not shown.

Every cylinder 204 has a Treibgasfüllraum 224 on. The propellant gas compartment 224 is between the piston body 220 , the piston front wall 222 and the cylinder 204 trained and changed with the position of the respective piston 214 , The one at the right cylinder 204 illustrated Treibgasfüllraum 224 is thus composed of a cylindrical section and an annular gap.

The propellant gas compartment 224 is over several overflow valves 226 with a propellant expansion room 228 connected. The propellant expansion space 228 changes with the position of the piston 214 and points to the right cylinder 204 its largest and the left cylinder 204 its smallest extent. The overflow valves 226 at the right cylinder 204 are closed and the left cylinder 204 opened. With opened overflow valves 226 can drive gas from the propellant gas space 224 into the respective propellant gas expansion space 228 stream.

Both pistons 214 are connected to each other via a common piston rod 230 firmly connected. The piston rod 230 is toothed on both sides, in two sprockets 232 intervene to force a piston 214 to convert into a torque. Every sprocket 232 is with a freewheel 234 connected, so that in each case only in one direction of rotation a torque on with the freewheel 234 connected wheel hub 236 is transmitted. With arrows is a direction of rotation 238 indicated, in which a torque is transmitted. Both freewheels 234 are chosen so that a torque always in the direction of this direction of rotation 238 each of a sprocket 232 on the appropriate hub 236 is transmitted. The hubs have a sprocket toothing and are via a chain drive 240 connected to each other to achieve a synchronization of the torque. An oscillating movement of the piston rod 230 can thus on the choice of the freewheel 234 always in a torque with the direction of rotation 238 be implemented. The torque generated in this way can be achieved via output shafts 242 removed and fed to another use.

In the operating position according to 2 LPG pressure volume is coming from a propellant gas reactor and controlled by an MSR on all ring channels 10 the expansion machine 202 at. The stroke direction is as shown in the 2 directed to the right.

The overflow valves 226 , Filling valves 212 and exhaust valves 208 are controlled regularly. When the pistons 214 and piston rod 230 have arrived at a left inner direction reversal point, so if the right cylinder 204 the piston end wall 222 for example at the filling valve 212 arrived, close at the right cylinder 204 the overflow valves 226 , open the filling valves 212 in the right ring channel 210 , as well as the exhaust valves 208 in the right cylinder head 206 and give a substantially expansionslose LPG filling the right Treibgasfüllraumes 224 free. At the same time - also regularly controlled - the overflow valves open 226 in the left flask 214 and thus open up an expansion process of the left previously filled LPG filling space 224 ,

This unfolds both pistons 214 their pushing or expanding forces adding each other to the right. The filling valves are controlled in line with the requirements of the MSR 212 closed again when the right filling space 224 filled and the piston 214 arrived in its extreme right position.

By filling thrust forces on the piston 214 , resulting from the Treibgasfülldruck multiplied by the effective annular area, the one end face of the annular gap of Treibgasfüllraumes 224 equivalent. This leads to a piston stroke. In the course of this stroke, which corresponds to the in 2 shown operating position, are the shear forces acting on the annular surface of the right piston 214 work consistently. The propellant gas does not yet expand in this step.

Through the opened overflow valves 226 at the left cylinder 204 Here, the propellant gas expands into the filling space 224 and results in expansion forces resulting from the instantaneous expansion pressure multiplied by the effective piston area. The effective piston area is the size of the circular area of the end face of the piston body 220 ,

The on the according to the representation of the 2 left piston 214 acting expansion forces are due to the falling pressure curve, ie the decreasing pressure initially very large, the maximum pressure approximately corresponds to the filling pressure, and may decrease to zero, when the pressure decreases to atmospheric pressure. In this case, there are no energy drains due to unused escaping residual pressure.

3 shows the expansion machine shortly before reaching the right inner reversal point, so shortly before the left Zylin of the 204 the piston end wall 222 the filling valve 212 has reached. At this point, the MSR gives the right exhaust valves 208 the closing command, as a result of which a residual propellant gas cushion builds up, which is the kinetic energy, from the moving linear unit, namely the piston 214 and the piston rod 230 , and this slows down to speed 0 and immediately accelerated linearly in the other direction.

While in the Compared to the state of the art in engines the necessary reverse acceleration forces of linear acting masses such as pistons, connecting rods etc. from the energy potential The flywheel mass must be taken, these forces are at the technology of the invention directly diverted and cause only a small reversal direction.

In 4 becomes the expansion machine 202 shown in an operating position with the lift left. At the left inner direction reversal point of the linear unit, namely the piston 214 and the piston rod 230 arrived, close the left spill valves 226 , open the filling valves 212 in the left ring channel 210 , as well as the exhaust valves 208 in the left cylinder head 206 and give the expansionslose propellant gas filling the Treibgasfüllraumes 224 free. At the same time, the overflow valves also open regularly 226 im according to the representation of 4 right piston 214 and thereby open up the expansion process of the right previously filled LPG filling space 224 ,

This unfolds both pistons 214 their thrust and expansion forces adding each other to the left. In the course of their stroke, the thrust forces on the annular surface of the left piston - resulting from the Treibgasfülldruck times the effective annular surface - are consistent. The on the right piston 214 acting expansion forces are initially very large as a result of the declining pressure curve, with the maximum pressure corresponds approximately to the filling pressure and can be reduced to ambient pressure with complete expansion. A positive torque input of approx. 96% is aimed for. If the expansion pressure builds up to ambient pressure, there are no energy outflows due to unused escaping residual pressure.

Just before reaching the left inner direction reversal point, as in the 5 is shown, the MSR gives the left exhaust valves 208 the closing command, as a result of which a residual propellant gas cushion builds up, which is the kinetic energy from the moving linear unit, consisting of the pistons 214 and the piston rod 230 , which decelerates to speed 0 and immediately accelerates linearly in the other direction.

With reaching the left inner direction reversal point is the with reference to the 2 to 5 previously described linear cycle at its starting point and begins a new linear cycle with the same process.

With this described linear cycle is the previously in the propellant gas reactor generated or converted thermodynamic energy into a linear mechanical Energy converted.

The double-toothed piston rod 230 has a toothing, the - according to 2 - top and bottom, each with a sprocket 232 is engaged. Moves the piston rod 230 to the right so arises in the upper sprocket 232 a left-turning torque and in the lower sprocket 232 a right turning torque. Moves the piston rod 230 to the left so arises in the upper sprocket 232 a right turning torque and in the lower sprocket 232 a left-turning torque.

Consequently is a torque conversion as optimal as possible, since the effective Lever arm always remains the same size and constructive wishes can be adjusted.

The freewheels 234 are between both sprockets 232 and the wheel hubs 236 , which have corresponding Kettenradverzahnungen arranged. The task of freewheeling 234 consists of turning the left-hand torques on the wheel hubs as shown here 236 to transmit, or the respective right-rotating torques not on the hubs 236 transferred to. If you want a right-rotating expansion machine 202 , so only the effective direction of freewheels 236 change.

The tasks of the wheel hubs 236 torque-fixed connected and radially, and axially mounted drive shafts, are to couple the generated torques - the generated powers of the expansion machine with other elements, or to forward to a power consumers on.

The chain drive 240 is provided for synchronizing the torques on both hubs, whose task is both output shafts 242 To synchronize torque-resistant and beyond a torque or power transfer of the total power either at both output shafts 242 to enable.

It should be noted that the 2 to 5 the same expansion machine 202 schematically even if there may be some differences in the size of the display. The 2 to 5 differ in the operating states shown in each case.

6A illustrates the interaction of the propellant gas generating device 2 with an expansion machine coupled thereto 202 , The propellant gas generating device 2 generates propellant in the two LPG reactors 5 , The propellant gas reactors 5 are with their propellant pressure vessels 4 with the cylinders 204 the expansion machine 202 coupled so that propellant gas from the outlet 18 the propellant pressure vessel the ring channels 210 is fed and so on the filling valves 212 provided.

The MSR 10 is for simultaneously controlling the propellant gas reactors 5 and the expansion machine 202 intended. It can be measured values from the propellant gas reactors 5 and the expansion machine 202 be taken into account. So a reading can be the pressure in the propellant gas space 224 be.

According to 6A is the direction of movement of the linear unit consisting of the piston 214 and the piston rod 230 directed to the right as shown and leads to a force and torque transmission over the upper sprocket 232 and the direction of rotation is directed to the left. In the 6B the direction of movement of the linear unit is directed to the left as shown and leads to a force and torque transmission over the lower sprocket 232 and the direction of rotation is also directed to the left. In both cases, the in 6A and 6B are shown, the torque is at the wheel hubs 236 directed left. The two sprockets 232 However, they turn in opposite directions and with changing directions.

The propellant gas reactor 705 of the 7 has a combustion chamber 706 with a burner 708 on. In the area of the burner 708 becomes the combustion chamber 706 Fuel via injectors 740 and combustion air via air inlets or air nozzles 737 fed. This is the fuel over fuel lines 739 and the combustion air via air ducts 735 fed.

Near the combustion chamber 706 is additional compressed air via compressed air supply 750 fed. This additional compressed air is supplied via compressed air lines 752 provided. This additional compressed air can also be referred to as secondary fuel, which lowers the temperature of the propellant gas and increases its volume.

Part of the compressed air supply lines 752 runs immediately outside the combustion chamber 706 and thereby forms for the combustion chamber 706 a second wall. As a result, on the one hand, the combustion chamber 706 thermally insulated to the outside, on the other hand also leads to a heating of the supplied in this double wall further compressed air. The compressed air is thus before feeding in the range of compressed air supply 750 warmed to the process in the propellant gas reactor 705 to favor.

Via supply lines 748 becomes the propellant gas reactor 705 Water and / or water vapor via feeders 749 fed under pressure. The feeders 749 are according to 7 still above the compressed air supply 750 arranged. The water should act essentially thermally in the generated propellant gas, but not directly on the combustion process in the combustion chamber 706 act. Part of the supply lines 748 be outside the combustion chamber 706 but inside an insulation wall 745 led, so that a further Doppelwandigkeit arises, the isolation of the propellant gas reactor 705 increases to the outside and at the same time to a heating of the water or water vapor in the supply lines 748 leads. The water or water vapor is thus heated to the propellant gas reactor 705 fed. The supply of water vapor leads to an increase in volume of the propellant gas with simultaneous reduction in temperature and the water or water vapor can thus also be referred to as another secondary fuel. In general, the term water may also mean water vapor.

In the combustion chamber 706 thus takes place by supplying fuel through the injectors 740 and combustion air via the air nozzles 737 a combustion caused by the supply of additional compressed air in the area of the compressed air supply 750 can still be supported. Here, a hot propellant gas is generated at a higher pressure and lower temperature. A further increase in volume and temperature reduction is achieved by supplying the water in the area of the water supply 749 reached. The propellant gas thus generated can finally through the outlet 718 the propellant gas reactor 705 leave and be supplied to another compound, in particular an expansion machine.

The propellant gas reactor 805 of the 8th has a propellant pressure vessel 804 on, whose interior 803 directly to a combustion chamber 806 followed. In the combustion chamber 806 is in the range of a burner 808 via a fuel injector 840 Fuel in the combustion chamber 806 directed. Combustion air is via air nozzles 837 also in the combustion chamber 806 initiated. After ignition, the fuel burns with the combustion air to a fuel gas in the combustion chamber 806 and gets from there further into the Treibgasdruckbe container 804 ,

The combustion chamber 806 and the interior 803 are essentially with a heat-resistant wall 860 surround.

Outside the heat-resistant wall 860 becomes a first secondary fuel via a first secondary fuel channel 851 fed. The secondary fuel channel 851 flows into first secondary fuel feeds 850 that are in the heat-resistant wall 860 are formed and supplying the first secondary fuel in the propellant pressure vessel interior 803 enable. In this area at the first secondary fuel feeds 850 the combustion process is already complete or at least substantially complete. The mixing of the first secondary fuel with the fuel gas leads to an increase in volume of the resulting propellant gas. In addition, the first secondary fuel absorbs heat from the fuel gas.

The first secondary fuel channel 851 is outwardly by a heat-resistant middle wall 862 limited. Outside this heat-resistant middle wall 862 is a second secondary fuel channel 871 arranged, a second secondary fuel to the interior 803 the propellant pressure vessel 804 and thus the propellant gas reactor 805 provides. According to the propellant gas reactor 805 of the 8th is intended to supply compressed air as the first secondary fuel and to supply water vapor as the second secondary fuel.

The second secondary fuel channel 871 flows into second secondary fuel feeds 870 that the second secondary fuel in the interior 803 can initiate. The second secondary fuel becomes the second secondary fuel channel 871 via a second secondary fuel line 872 fed. In this case, by means of the second secondary fuel line 872 the second secondary fuel around a propellant gas outlet 818 in several turns 874 guided, so that possibly the second secondary fuel can be preheated here by heat-emitting propellant gas. Depending on the design can be in the range of these turns 874 from pressurized water, water vapor is formed.

The second secondary fuel channel 871 is from an outer heat-resistant wall 864 surrounded, in turn, by a pressure-resistant housing 866 surrounded, thus the combustion chamber 806 and the interior 803 essentially completely closes. Finally, the pressure-resistant housing 866 around an insulation 868 intended. It should be noted that the insulation is intended in particular to leave heat in the system in order to avoid energy losses. In principle, protection against overheating is achieved by using existing heat to increase the volume of the propellant gas.

The expansion machine 902 of the 9 includes two expansion subassemblies 903 , Each expander subassembly 903 has a cylinder 904 and a piston guided therein 914 on. In the cylinder 904 is a propellant expansion space 928 provided for filling with propellant, so that it expands there and to a movement of the piston 914 leads. Furthermore, in the cylinder 904 a compression room 925 provided, which is used for compressing air use. The two pistons 914 are via a piston rod 930 mechanically firmly coupled with each other. The piston rod 930 has a toothing on two sides, with which they engage with two sprockets 932 is. The sprockets 932 change their direction of rotation depending on the direction of movement of the piston rod 930 , About freewheels 934 becomes an oscillating movement of the piston rod 930 in a torque with only one direction of rotation at the wheel hubs 936 and thus the associated drive shafts 942 transformed. For a synchronization of the wheel hubs 936 is a chain drive 940 intended.

Below is on the two expansion sub-assemblies 903 as right and left expansion sub-assembly reference, wherein the terms right and left to the representation according to the 9 Respectively. To operate the expansion machine 902 For example, on the left side, propellant gas is delivered via a fill valve 912 the propellant expansion space 928 fed. The propellant gas then expands in the propellant gas expansion space 928 and thus leads to a movement of the left piston 914 to the right. The propellant expansion space 928 increases thereby, whereby the compression space 925 reduced and leads to a compression contained therein air. In this left compression space 925 was previously through the air filling valve 962 Admitted air, which is now compressed. After desired compression, the compressed air from the compression chamber 925 via the air outlet valve 958 discharged and a desired use, in particular a propellant gas generating device are fed as secondary fuel or combustion air.

The described movement also leads to a movement of the piston rod 930 to the right, which leads to a left turn of the upper sprocket 932 and a clockwise rotation of the lower sprocket 932 leads. During this movement, the left turn of the upper sprocket becomes 932 in a torque with left turn on the upper wheel hub 936 transformed. Due to the freewheel 934 leads in the lower sprocket 932 to stop the movement torque at the wheel hub 936 , Rather, this turn the lower sprocket 932 and the lower wheel hub 936 in opposite directions.

By coupling the two pistons 914 is due to the expansion of propellant gas in the left propellant expansion space 928 also to a movement of the right piston 914 to the right, leaving the right propellant gas expansion space 928 reduced. Here is the outlet valve 908 opened, so that propellant thereby the right Treibzasxpansionsraum 928 leaves. This propellant gas optimally has atmospheric pressure, but at the same time still has a relatively elevated temperature to the environment. That from the exhaust valve 908 escaping propellant gas is thus a heat exchanger 970 fed. In the heat exchanger 970 Heat of the propellant gas can be delivered to water, whereby the water can be heated and used as a further, in particular second secondary fuel and fed to a propellant gas generating device.

Due to the movement of the right piston 914 to the right also increases the compression space 925 in the right cylinder 904 and it can air there through the air fill valve 962 in the compression room 925 flow.

The two over the piston rod 930 coupled pistons 914 form a movable linear unit and these two coupled pistons 914 are also referred to as free pistons. To dampen the described, rightward-directed motion may be in a position before a piston end wall 922 reaches a cylinder head, the right exhaust valve are closed before reaching the end position of this free piston, so that a residual amount of propellant gas in the right Treibzasxpansionsraum 928 remains and forms a gas cushion.

One A central component of the invention is a propellant gas reactor whose Task it is under as possible optimal utilization of the heat energy contained in the fuel to generate a maximum propellant gas volume flow under high pressure, to feed it to a downstream machine.

The Adaptation to different power states of the entire machine so a combination of the propellant gas reactor with an expansion machine or the like is done by appropriate change of the supplied fuel, Combustion air and SKT quantities.

The Maximizing the propellant gas flow rate should be under consideration the temperature compatibility at the outlet of the reactor - and at Inlet of the machine - used Materials by using compressed air as combustion air, secondary fuels (SKT) in the form of compressed air, water or steam.

Of the Propellant gas reactor consists of a heat-insulated, pressure-resistant Outer shell. Central at the bottom, fuel and combustion are added increased Pressure necessary combustion air supplied to a chamber, in the combustion process can take place completely.

By further inlets SKT's can be fed in the form of additional compressed air, water or water vapor and fed to the combustion gas as for an embodiment in 8th is shown. The propellant gas thus produced leaves the reactor through an opening in the upper area and serves to drive a machine, in particular an expansion machine.

in the Ideally, these SKT's so fed that their volume flows the outer reactor wall from overheating protect. Optionally, the use of a high temperature resistant lining the combustion chamber necessary.

9 also illustrates that the propellant gas from a propellant gas generator 900 comes, which is briefly referred to as a reactor. This propellant gas generating device 900 fuel and combustion air are supplied, as well as a first secondary fuel SKT1, as compressed air through the compression chamber 925 can be provided, and a second secondary fuel SKT2, in the heat exchanger 970 can be prepared and provided as heated water or steam.

The heat engine 1000 of the 10 to 12 includes two propellant gas reactors 1005 that with an expansion machine 1102 are coupled. In the propellant gas reactors 1005 a propellant gas is generated, each via an outlet 1018 and an adjoining propellant gas supply 1019 each of an expansion sub-assembly 1103 can be supplied. In the expansion subassembly 1103 can the propellant gas basically via a filling valve 1112 a propellant expansion space 1128 be supplied. After any expansion, the propellant may be exhausted 1108 be drained again. Here is the exhaust valve 1108 an outlet pipe 1109 downstream.

By an expansion of propellant gas in the propellant gas expansion space 1128 each one of the expansion sub-assemblies 1103 increases the corresponding propellant gas expansion space 1128 and moves a piston 1114 via a piston end wall 1122 , The two pistons 1114 are via a piston rod 1130 mechanically coupled and one Movement of the pistons 1114 and thus the piston rod 1130 leads to a conversion into a torque in the conversion mechanism 1144 , The functioning of the conversion mechanism 1144 corresponds approximately to that in connection with the expansion machine according to 9 described.

By a movement of the pistons 1114 and the piston rod 1130 - which together form a linear unit - also becomes the volume of the compression spaces 1125 changed. Moving from the 10 this linear unit as shown to the right, so the left compression space decreases 1125 and leads to compression of air contained therein, which can thus be provided as compressed air. This compressed air can be connected to an air outlet valve 1158 be removed. At the same time, the right compression space increases 1125 and air can pass through the air fill valve 1162 in the compression room 1125 flow.

The propellant gas reactors 1005 are operated with a fuel and combustion air. The fuel is by means of a fuel or fuel pump 1038 and a fuel valve 1026 supplied to control the fuel or fuel supply. The combustion air is as compressed air through the expansion machine 1102 provided, wherein the compressed air as described in the area of the air outlet valves 1158 provided. This compressed air is the propellant gas reactor 1005 also as the first secondary fuel outside the combustion chamber 1006 through the first secondary fuel supply 1050 fed.

Furthermore, water vapor is used as the second secondary fuel in the second secondary fuel feeds 1070 fed. The second secondary fuel is first through a water pump 1042 and water flow control valve 1030 provided with pressure. Before the feed to the propellant gas reactor 1005 However, a preheating is first carried out by appropriate Leitungswindungen 1076 in the area of the LPG outlet pipe 1109 through which the propellant gas from the propellant gas expansion space 1128 flows. Further heating of the water in particular to the water vapor then takes place in further turns 1074 in the field of propellant gas supply 1019 that are at the outlet 1018 the propellant gas reactor 1005 followed. The water thus heated, in particular heated to steam, is then used as second secondary fuel by the second secondary fuel feeds 1070 the propellant gas reactor 1005 fed.

The 11 and 12 illustrate again - starting from the 10 - A movement of the linear unit, consisting of the two pistons 1114 and the piston rod 1130 is formed, to the right as shown. This is also to illustrate the pressure distributions. According to 10 is propellant in the propellant gas expansion space 1128 been introduced on the left side. From 10 above 11 to 12 This propellant gas now leads to an increase in volume of the left propellant gas expansion space 1128 and thus a pressure decrease of the propellant gas contained therein. At the same time takes place in the left compression space 1125 a pressure increase of the air contained.

At the same time, propellant gas from the right Treibzasxpansionsraum 1128 ejected, wherein the pressure of the propellant gas remains substantially the same there, namely approximately equal to atmospheric pressure. Also the pressure in the compression room 1125 in the right cylinder 1104 remains essentially constant, namely at about atmospheric pressure, since air through the air filling valve 1162 flows. After reaching the position according to 12 The process reverses and the linear unit will turn left again.

Moreover, in the 10 to 12 a central measuring, control and control unit 1010 shown. This measuring, control and control unit 1010 , abbreviated as MRS 1010 is designated, is used to control both the propellant gas generating device, so also the fuel pump 1038 , the fuel valve 1026 and the water pump 1042 and the water control valve 1030 used, as well as for controlling the expansion machine, so in particular the valves. In addition, the conversion mechanism 1144 a controlled freewheel or clutch freewheel, which also by the central MRS 1010 is controlled. The central MRS 1010 can also be used to heat several engines according to the 10 to 12 to pair. In this case, the MRS takes over 1010 also a synchronization control, so that the heat engines, in particular the expansion machines with the same frequency or based on the resulting torque at the same speed but shifted phase are operated. As a result, a mechanical synchronization coupling can be avoided, whereby the operation of one and in particular a plurality of heat engines is flexible and in particular variable.

The heat engine 1300 of the 13 comprises a propellant gas generating device 1301 with two propellant gas reactors 1305 and one.

expander 1302 with a conversion mechanism 1344 , This heat engine 1300 corresponds substantially to the heat engine according to the 6A and 6B , where additionally a compressor 1350 provided and about the conversion mechanism 1344 with the expansion machine 1302 is coupled.

The compressor 1350 has two first compression chambers 1352 and two second compression rooms 1354 on. Every second compression room 1354 is in a compression body, namely compression piston 1356 formed, the compression piston 1356 via a rack section 1358 mechanically firmly coupled together and basically a moving body 1360 form. Each of the first compression rooms 1352 is in a cylinder jacket 1362 formed by the respective compression piston 1356 emotional.

Hereinafter, the operation of compressing a gaseous medium such as air is described, with directions such as right and left to the representation according to the 13 Respectively. Basically everyone forms the first compression space 1352 a first compression stage and every second compression space a second compression stage. According to the presentation of the 13 the compression piston moves 1356 to the left and compresses air in the first compression space 1352 the left side, previously through compressor intake valves 1364 has flowed. At this compression in the first compression space 1352 on the left side air flows with increasing compression through connecting valves 1366 in the second compression space 1354 , It will be the first compression stage in the left part of the compressor 1350 performed.

In the right part of the compressor 1350 is the second compression stage according to the operating position in the 13 carried out. Already compressed air is in the second compression space 1354 this right side and is caused by the left-hand movement of the compressor piston 1356 further compressed by the second compression space 1354 due to the movement of the compressor piston 1356 reduced. The air compressed in this second stage can be passed through a compressor outlet valve 1368 in a Kompressorauslassbereich 1370 arrive from there and finally fed to another use.

In the mentioned movement of the compression piston 1356 In addition, the first compression space increases in the right part 1352 and air can pass through the compressor inlet valves 1364 inflow to simultaneously prepare a first stage of compression. At the compressor 1350 is the moving body 1360 that made the two compression pistons 1356 and the rack section 1358 basically the only moving part, with the exception of the moving elements of the valves. The moving body 1360 thus moves relative to the cylinder jacket 1362 and the compressor discharge area 1370 , For generating the oscillating motion of the moving body 1360 this is over the rack section 1358 with the upper sprocket 1332 the conversion mechanics 1344 coupled, with the sprocket 1332 through the piston rod 1330 the expansion machine 1302 is moved. Thus, the movement of the moving body 1360 of the compressor 1350 opposite to the movement of the piston rod 1330 the expansion machine 1302 ,

For the rest of the operation of the heat engine is on the description of other embodiments including the embodiments of 6A and 6B directed. The through the compressor 1350 generated compressed air can in the propellant gas reactors 1305 For example, be used as combustion air or as a secondary fuel.

Also to the 13 It should be noted that the representation is schematic and does not allow any conclusion about any size relationships.

The change mechanics 1444 of the 14 has two sprockets 1432 on, which is rotatable in a housing 1446 are stored. Adjacent to each sprocket 1432 is ever a flywheel 1431 represented fixedly connected to the respective ring gear to store rotational energy. Further flywheel masses are each provided on the same axis, which in the 14 but are not recognizable. These inertia masses increase the corresponding moment of inertia in order to be able to store correspondingly more rotational energy. Between the two sprockets 1432 is a first toothed piston rod 1430 a first expansion machine and is equipped with two sprockets 1432 engaged. A second piston rod 1429 a second expansion machine is only with a sprocket 1432 engaged. The piston rods 1429 and 1430 move in opposite directions and according to the presentation of the 14 is the first piston rod 1430 in a leftward moved position and correspondingly the second piston rod 1429 shown in a moved to the right position. The movement of the first piston rod 1430 is placed directly on the upper or lower sprocket 1432 transfer. The movement of the second piston rod 1429 becomes directly on the lower sprocket 1432 transmitted and over the lower sprocket, the first piston rod 1430 indirectly on the upper sprocket 1432 , Wherein said directions are based on the representation according to the 14 Respectively.

The rotation of the sprockets 1432 depending on the direction through the upper or lower sprocket 1432 transferred into a torque.

The force and torque effects are in 15 illustrates, therefore, the upper piston rod 1430 can exert a force F1 with changing direction and the second piston rod 1429 a force F2 also with changing direction. Leads the first piston rod 1430 one - related to the representation of the 15 - rightward force F1 off, so this is on the upper sprocket 1432 transferred to a left-handed torque M1, which continues on the wheel hub 1436 is transmitted. Here exercises the second piston rod 1429 a left-handed force F1, which is transmitted to the lower ring gear 1432 , from there to the first piston rod 1430 and from there on to the upper sprocket 1432 where it leads to a left-facing torque M2. The torques M1 and M2 add up.

Is the force F1 of the first piston rod 1430 directed to the left, so this is on the lower sprocket 1432 as left-directed torque M1 and from there on to the wheel hub 1436 about asking. Here, the force F2 of the second piston rod 1429 directed to the right and is directly on the lower sprocket 1432 transferred there and leads there to a left-facing torque M2. Again, the torques M1 and M2 add up. It should be noted that the wheel hubs 1436 over a chain drive 1440 are coupled and corresponding torque optionally on the upper and / or lower wheel hub 1436 can be removed. According to this embodiment, a coupling of two expansion machines with only one conversion mechanism can be achieved in a simple manner. It only needs a second guide for the second piston rod 1429 be provided.

The propellant gas reactor 1605 according to the embodiment of the 16 works with a fuel and combustion air and three secondary fuels, namely compressed air as the first secondary fuel SKT1, water vapor as the second secondary fuel SKT2 and water as the third secondary fuel. A measuring, control and control unit 1610 , short as MRS 1610 denotes the supply of said five substances. A compressor 1636 generates compressed air and also has a compressed air tank for storing compressed air. The compressed air is the MRS 1610 fed and there on the one hand as combustion air for combustion in the combustion chamber 1606 provided on the other hand as the secondary fuel SKT1 the propellant gas reactor 1605 fed. Water reaches the MRS 1610 under pressure and from there directly to the propellant gas reactor 1605 supplied and on the other a heat exchanger 1680 supplied, so that the water is the heat exchanger 1680 leaves as water vapor and thus as the second secondary fuel SKT2 the propellant gas reactor 1605 can be supplied. The heating in the heat exchanger 1680 carried out by propellant, which is the expansion machine shown 1602 leaves. After the propellant gas in the heat exchanger 1680 Heat has given off to the water, this leaves the heat exchanger 1680 ,

In the propellant gas reactor 1605 is the combustion chamber 1606 arranged and protected by a heat-resistant wall 1660 surround. Outside the heat-resistant wall 1660 the water flows from a central wall 1662 is surrounded. Outside the middle wall 1662 Partially, the first secondary fuel SKT1 and partly the second secondary fuel SKT2 flow. Finally, the propellant gas reactor, in particular the guidance of the first and second secondary fuel from the outer wall 1664 enclosed. The first and second secondary fuels SKT1 and SKT2 are piped 1669 through the middle wall 1662 , essentially across the channel 1661 and through the heat-resistant wall 1660 through to the interior 1603 the propellant gas reactor 1605 directed. Continue to the outlet 1618 the propellant gas reactor 1605 towards first the water is added to the propellant gas. In the direction of flow of the propellant gas, subsequently, there is a boundary wall 1617 basically in the outlet 1618 intended. Subsequently, the propellant gas is supplied via corresponding lines of the expansion machine. Preferably, the third secondary fuel is supplied to the propellant gas reactor in a start-up phase. The second secondary fuel is preferably supplied after the start-up phase and the supply of the third secondary fuel is thereby reduced.

17 shows a cylinder head 1701 an expansion machine. On the cylinder head 1701 is a jacket pipe 1702 arranged by turn a cylinder 1703 is arranged. In the cylinder 1703 becomes a piston 1704 movably guided. In the flask 1704 is a so-called compression piston 1741 arranged, in principle, firmly with the piston 1704 connected is. In flight with the upsetting piston 1741 is a chamber with lubricating oil or compression damping oil 1705 arranged.

During the intended movement of the piston 1704 in the cylinder 1703 Propellant flows through an inlet valve 1706 in the cylindrical space in which the piston 1704 moves and pushes the piston 1704 according to the representation of 17 to the left. The piston returns 1704 back, that's the inlet valve 1706 closed and an exhaust valve 1707 open. Propellant gas is then passed through the piston 1704 from the outlet at the outlet valve 1707 pushed out. To do this, the piston 1704 In its movement, the exhaust valve can 1707 before reaching the end position by the piston 1704 be closed, so that a damping cushion is formed by the remaining propellant, which the piston 1704 cushioning and at the same time be in the opposite direction be can accelerate.

Should a malfunction occur, for example, this before closing the exhaust valve 1707 failed, the piston would 1704 continue his movement and damage the cylinder head 1701 stocks. To cushion this is an emergency compression chamber 1711 provided, in which the piston 1704 then move. Once the piston with a front end at the beginning of the emergency compression chamber 1711 arrived, this leads to a forced closure of the channel 1709 of the inlet valve 1706 and the duct of the exhaust valve 1707 , The piston is then in the emergency compression chamber 1711 cushioned.

Another safety measure is the chamber with the lubricating oil or compression damping oil 1705 intended. Should the damping through the emergency compression chamber 1711 not enough, so can the compression piston 1741 basically from the movement of the remaining piston 1704 and continue into the chamber with the compression damping oil 1705 arrive and be damped there.

Incidentally, between the casing pipe 1702 and the cylinder 1703 a temperature compensation space provided in which, if necessary, a thermal filling is present, the temperature compensation along, ie in the longitudinal direction of the cylinder 1703 , to achieve, in particular a compensation of high temperatures in the area of the cylinder head 1701 in the opposite direction of the cylinder 1703 ,

The piston 1801 in the 18 is with a compression piston 1802 provided with shear pins 1803 are firmly connected. In the flight of the compression piston 1802 is a compression cylinder 1806 arranged in the upsetting piston 1802 basically partially used. A seal is made by means of the sealing ring 1804 , During normal operation, the compression piston moves 1802 thus together with the piston 1801 , The piston 1801 is doing in a cylinder, not shown by means of the guide rings 1805 guided. For lubrication of the piston 1801 is lubricating oil via a lubricating oil supply 1808 the compression space 1806 fed. About lubrication leaks 1809 the lubricating oil reaches the outside of the piston 1801 and can this against a cylinder in which the piston 1801 is guided, lubricate. Incidentally, this is the piston ring set 1807 intended.

In case of malfunction in which the piston 1801 through the upsetting piston 1802 in his movement further than desired according to the representation of 18 pushed to the right and against a particular obstacle pushes a cylinder head, the shear pins 1803 break and the force from the upsetting piston 1802 can through the lubricating oil in the compression space 1806 be attenuated, this in this case by the Schmieraustritte 1809 can be pushed out.

In a cylinder tube 1902 becomes propellant in an interior 1901 guided or it can exert force on a piston, not shown there. Outside the cylinder tube 1902 is an annular gap 1903 provided with a thermal oil filling to temperature along the cylinder tube 1902 especially in the longitudinal direction to distribute or compensate. The annular gap 1903 is through a jacket pipe 1904 limited. Around the jacket pipe 1904 is an insulation material 1905 arranged, in turn, in an outer tube 1906 is included. Only from the outer tube 1906 out to the outside, a temperature output takes place out of the system, wherein on the outer tube 1906 with a temperature in the range of 30 ° C is expected.

Explanation to drawing no. 1.00.1 or 20 :

(Alternative reference numbers in parenthesis)

• Pos. 1 reactor foundation with full insulation ( 2001 )
• Pos. 2 reactor body ( 2002 )
• Pos. 3 intermediate frame ( 2003 )
• Pos. 4 header and collection plate ( 2004 )
• Pos. 5 insulating cover ( 2005 )
• Pos. 6 Propellant condensate treatment ( 2006 )
• Pos. 7 Valve for the power control ( 2007 )
• Pos. 8 Valve for condensate vapor pressure ( 2008 )
• Pos. 9 storage tank ( 2009 )
• Pos. 10 working pressure measuring system ( 2010 )
• Pos. 11 Heat source (gas oil burner etc.) ( 2011 )
• Pos. 12 exhaust control ( 2012 )
• Pos. 13 Capacitor ( 2013 )
• Pos. 14 Condensate pump ( 2014 )
• Pos. 15 Insulation housing ( 2015 )
• Pos. 16 Central power and machine control system ( 2016 )
• Pos. 17 Fuel line network ( 2017 )
• Pos. 18 propellant injection nozzles ( 2018 )
• Pos. A fuel supply line
• Pos. B air supply line
• Pos. C1 working pressure line
• Pos. C2 overpressure discharge line ends in C1
• Pos. D exhaust / condensate collector
• Pos. E compressed air connection line
• Pos. F exhaust pipe

Component description for drawing 1.001:

Pos. 1:

The Foundation with thermal full insulation carries the reactor body, as well its superstructures and isolated the heat radiation of the combustion chamber downward.

Pos. 2:

Of the reactor body consists of a good heat-conducting Material (copper, or similar) and is alternated with heating gas ducts (pressureless) and propellant gas ducts (pressurized) interwoven. The drawing shows in the right half section the course of the Propellant or Treibgasverlaufes and in the left half cut the Course of the hot gases.

Pos. 3:

Of the Intermediate frame of good thermal conductivity Material leaves a cavity between the reactor body and the head and collection plate (Pos 2 and 4) arise in which the Treibmittelleitungsnetz (pos. 17) and the connections the propellant injectors (Pos. 18).

Further the space is used as Heizgasumlenkkammer and serves the additional preheating of the Propellant before its injection into the reactor.

Pos. 4:

The Head and collection plate forms the upper end of the reactor core and collects all propellant gas channels of the reactor core the connecting tubes to the reactor core to one or more central Working pressure line (s) (C1).

Of Further features the head and collection plate over the necessary breakthroughs for the passage of hot gases upwards.

Pos. 5:

Of the Insulating cover forms the upper thermal termination of the reactor core and isolates this against the otherwise occurring Körperkontaktwärmeabfluss up.

Of the Insulating lid has the necessary breakthroughs for conducting the hot gases into the reactor cavity in which the Pipe network for the condensate preparation (item 6) is located.

Pos. 6:

The Condensate treatment plant consists essentially of a pipe network that is about 75% filled with condensate is and the residual energy of the reactor core leaving the hot gases largely deprives to optimally preheat the condensate.

Via the valve for the power control (item 7) and the connecting cable 17 the condensate at about 60 bar pressure is fed to the propellant injection nozzles (item 18). Any excess pressures (greater than 60 bar) are fed via the control valve (Pos. 8) and the line C2 to the expansion part of the WWKM.

Pos. 7:

In Cooperation with the central power and machine control system and the heat and pressure sensors WWKM primarily regulates this valve the flow rate of the propellant, the volume or the pressure of the propellant gas can arise in the reactor core, whereby the performance of the WWKM plant is regulated.

Pos. 8:

The Valve for the condensate steam overpressure directs any overpressure via the pressure line C2 off and leads beneficial to the expansion part of the WWKM plant.

Pos. 9:

Of the Storage pressure vessel cares about its valves for that even after the standstill and the cooling of the WWKM plant enough propellant pressure pending to start the system again.

Pos. 10:

The Working pressure measuring system is used to record the current working pressure and associated with the central machine control for regulation and control of the inlet valve (item 9 expansion plant) of the expansion plant.

Pos. 11:

The heat source is the power supply of the WKM machine, it can be very different Be kind. Nowadays, this heat source can burn through of gases, oils or coals, but also produced by atomic energy.

There the burning of the v. G. Energy sources only under atmospheric Pressure can happen, this can be particularly effective and environmentally friendly be regulated and controlled.

Pos. 12:

The Exhaust control system ensures a thermally and vacuum controlled pipe or drain and optimal utilization of the hot gases.

Pos. 13:

The condenser takes up the utilized pressureless propellant gas of the expansion system via the manifold D and cools it only as far which in turn results in the warmest possible liquid propellant.

Pos. 14:

The Condensate pump takes the condensed propellant from the condenser unpressurized and promotes it into the pressurized condensate treatment plant.

Pos. 15:

The insulating housing isolates the entire reactor against heat loss to the outside.

Pos. 16:

The Central power and machine control system controls all Machine conditions and regulates and controls all machine and performance parameters, as long as these are not exclusive be controlled in synchronous rotation.

Pos. 17:

The Treibmittelleitung leads the propellant over the control valve (item 7) the propellant injection nozzles in the reactor core to.

Pos. 18:

The Propellant injectors atomize the propellant as much as possible Fine foggy in the heated propellant gas channels, causing almost explosive the propellant gas is produced.

Explanation to drawing 2.00.1 or 21 and 22 :

Title: Heat engine expansion part

(Alternative reference numbers in parenthesis)

• Pos. 1 Machine foundation with machine housing ( 2101 )
• Pos. 2 bearing blocks for 3 shafts ( 2102 )
• Pos. 3 toothed segment gears interlocked approx. 180 ° ( 2103 )
• Pos. 4 gears for synchromesh gears ( 2104 )
• Pos. 5 connecting rod bilateral toothed ( 2105 )
• Pos. 6 piston rods ( 2106 )
• Pos. 7 piston ( 2107 )
• Pos. 8 Cylinder complete with heads and feet ( 2108 )
• Pos. 9 Inlet valves synchronous and power controlled ( 2109 )
• Pos. 10 outlet valve synchocontrolled ( 2110 )
• Pos. 11 reversing valve synchronous controlled ( 2111 )
• Pos. 12 spring accumulator cpl. ( 2112 )
• Pos. 13 Shafts / freewheel shafts ( 2113 )
• Pos. 14 Central shaft / output shaft ( 2114 )
• Pos. 15 synchronous rod drive cpl. ( 2115 )
• Pos. 16 Piston rod seal and bearing ( 2116 )
• Pos. 17 Piston seal and bearing ( 2117 )
• Pos. 18 output shaft seal ( 2118 )
• L = approx. Length the machine here 7,300 mm
• H = approx. Height the machine here 2,700 mm
• BF = approx. Width of the machine foundation here 1.700 mm
• BG = approx. Width of the machine housing here 1,400 mm
• D = cylinder diameter here 500 mm
• d = piston rod diameter here 493 mm
• r = effective radius of the toothed segment wheel here meshed 500 mm / 180 °
• D = collecting and connecting line to the condenser
• C = propellant gas line to the reactor part / controller

Component description for drawing 2.00.1:

Pos. 1:

The Machine foundation with the machine housing forms the outer frame the machine and the connection to the cylinders.

Pos. 2:

The bearing blocks stand on the machine foundation and include the bearings the machine waves.

Pos. 3:

The Ratchet wheels create the form-fitting Connection of the rack with the machine shafts or their freewheel at the respective return stroke the machine.

Pos. 4:

The Equally dimensioned gears create in the connection shown with the shafts and the toothed wheels the Force or torque transmission from the power-generating linear units to the output shaft and synchronize all parts to each other.

Pos. 5:

The Connecting rod connects both piston rods with each other and directs the generated forces in the toothed segment wheels from.

Pos. 6:

The Piston rods form together with the pistons and their seals and the cylinders, the force-generating linear units.

Pos. 7:

The Pistons contain the reversing valves and are part of the linear units.

Pos. 8:

The Cylinder complete consist of the cylinder tubes in which the pistons with their seals running, as well as from the cylinder heads with the exhaust valves and the cylinder feet with the piston rod seals and inlet valves.

Pos. 9:

The Inlet valves become synchronous at the time of intake - and at Closing time controlled by the machine control.

Pos. 10:

The Exhaust valves are controlled synchronously.

Pos. 11:

The Reversing valves are controlled synchronously. In the open State they take care of the then released pressure equalization between the propellant volume on the piston rod side and the cylinder head side, thereby causing the area difference the powerful return stroke, in the connection of the propellant gas expansion and the likewise here resulting pressure reduction to approximately depressurized and the propellant gas recooling due the expansion cold, takes place.

Pos. 12:

Of the Spring accumulator stores the kinetic energy resulting from the movement and the mass of the linear unit results in the short term in the direction reversal the linear unit and leads Turn it on again after changing direction.

Pos. 13:

The Shafts / freewheel shafts accomplish together with the bearings and the Zahnsegment- and the gears, the conversion of linear forces into torque or as a result of the speed in engine power.

Pos. 14:

About the Central shaft, which is part of the wave system becomes the synchronization the machine parts brought about each other and the torque or the machine output to the outside dissipated.

Pos. 15:

The The task of the synchronous rod drive is to be seen exclusively in the linear unit at the time of the change of direction with the wheels running around synchronize.

Pos. 16:

The Task of the piston rod seal and storage is to ensure that no propellant volume balance takes place past them and the piston rods smooth be stored.

Pos. 17:

The Task of piston sealing and storage is to ensure that no propellant volume balance takes place past them and the pistons smoothly be stored.

Pos. 18:

The The task of the output shaft seal is to lubricate the Machine in the housing interior lubricant must not escape to the outside.

Overall function description of the heat engine:

The Initial situation of this description of the machine is like drawing shown in drawings 1.00.1 and 2.00.1, the reactor is pressureless and cold. The graphically illustrated situation is called the angle of rotation 0 ° designates.

• 1. Compressed air boiler (reactor R. Pos. 9) with Fill approx. 60 bar compressed air and thus put the propellant plant under pressure.
• 2. heat source (Burner R. Pos. 11) and thus the reactor core to the specified temperature Preheat. The hot gases are in the further course of their way through heat the reactor and the propellant system (R. Pos. 6) and this additionally due to the expansion of the propellant Put pressure.
• 3. About The machine control can now control the valve (R. Pos. 9) be, causing propellant over the propellant network (R. Pos. 17) and the propellant injection nozzles (R. Pos. 18) into the propellant gas channels is injected, which there due to the heat explosively propellant gas volume can arise. This propellant gas volume is now in the collection plate (R. Pos. 4) together and over the working pressure measuring system (R. Pos. 10) and the connecting line C1 supplied to the expansion plant.
• 4. This propellant gas volume is now developing gig the movement resistance of the expansion system pressure volume which acts via the left open inlet valve (expansion part, hereinafter called E. Pos. 9) on the annular surface of the left piston (E. Pos. 7) acts and this moves in motion to the left.
• 5. Due to the connection of the components piston (E. Pos. 7), Piston rods (E. Pos. 6) and the connecting rod (E. Pos. 5) becomes a coherent one Linear unit created, the mutually directional with each the responsible Zahnsegmentrad toothed engaged and thus each of the the linear unit and the working pressure developed force in the Ratchet wheels diverts or diverts and thereby in the waves / freewheeling waves (E. pos. 13) with which they are connected torque-tight generates a torque. On the shafts (E. Pos. 13) are also connected torque-resistant the same size gears for the Synchromeshiebe (E. Pos. 4), which the respective reciprocal Torque same direction of rotation, on the central synchronous wheel (E. Pos. 4), which is also torque-fixed connected to the central shaft / output shaft (E. Pos. 14) is transferred. About the Central shaft / output shaft (E. Pos. 14) can now each mutually linear forces in a direction of rotation equal torque / power converted to derived outside, or used there.
• 6. When reaching the first left reversal point takes the spring accumulator (E. Pos. 12) on the kinetic energy of the entire linear unit and deflects them 180 °. At the same time all valves change their switching states, whereby now the over the left circular area standing pressure volume on the structurally given X times larger differential pressure surface acts and thus supports the linear unit of the left spring store and from the right circular ring surface and the upcoming working pressure additionally driven the linear unit drives to the right. statement all valves: With the exception of the inlet valves (E. Pos. 9) are all Valves synchronous (depending on angle of rotation) controlled that means They change their respective switching states exactly at the time of one every change of direction of the linear unit.
• 7. However, the inlet valves always open (synchronous controlled) exactly at the time of the respective change of direction of the respective Direction of action to the outside, the possibly working pressure-dependent closing time However, is the central machine control (R. Pos. 16) on the the following direction change outgoing influenced, so always enough Expansion pressure volume for the expansion stroke is available whereby no vacuum losses until the following change of direction can enter.
• 8. Also at exactly the time of the first change of direction leaves upper Zahnsegmentrad the engagement in the upper toothing of the connecting rod and the lower Zahnsegmentrad engages in the lower part of the toothing the connecting rod and takes over so that the force or torque transmission, like this one below Point 5 explained has been. At the time of the clock change as described above (Linear unit Change of direction), change of valve switching states and change of force or torque coupling of connecting rod and respective Toothed segment wheel) are 90 ° of the angle of rotation the WWKM completed.
• 9. While the following cycle, another 180 ° rotation angle of the machine take place, wherein the lower toothed segment wheel with the lower toothing of the connecting rod are engaged and as described above for the force or torque flow analogous to guaranteed below is.
• 10. At 270 ° rotation angle Once again, the clock change, as described above, takes place analogously (Change of direction of the linear unit connected with simultaneous Change of force-torque flow from the lower to the upper segment of the toothed segment and valve switching) for the following 180 ° rotation angle, which then more than 360 ° functional sequence conclusive were presented and thus the following almost infinite functional sequence is described.
• 11. Since to the present Time can not be ruled out that by the constructive shaping the toothing of the connecting rod and the teeth toothed segment wheels a sufficiently secure synchronization of the linear unit with the rotating parts If necessary, the synchronous rod drive can be ensured for the necessary synchronization when clock change provide. Also possible It equipped the toothed segment with a return freewheel system so that Ratchet wheels constantly can remain in engagement with the teeth of the connecting rod (This construction is not shown in the drawing).

Evaluation and comparison of conventional systems Engines and a heat engine - after following as WWKM - according to at least a preferred or desired embodiment:

• 1. Unlike all engine types must the WWKM are not cooled at any point to protect against thermal damage.
• 2. The propellant gas reactor and the expansion engine (cylinder) should be well insulated against heat loss become.
• 3. In contrast to all engine types, the WWKM develops at every rotation angle as a result of the con constant lever arm (r) a torque. All engines have at about the time of their largest release of force as a result of Kurbelwel len torque generation lever arm length goes to 00 and as a result produces almost no torque.
• 4. Unlike all engine types, WWKM develops in each angular position force, torque and thus power, she is a true one-act. Even as a double investment is the WWKM capable of only slightly fluctuating To deliver torque.
• 5. Unlike all engine systems, the generated LPG pressure completely degraded at the WWKM and thereby profitably converted into torque or power.
• 6. The WWKM technology is predestined for making very large High torque and low speed performance. Becomes the WWKM technology for the drive always used the same speed and power, so can, if it positively influenced the efficiency, for propellant gas generation also a conventional steam boiler can be used. The one shown here Reactor technology allows a relatively fast speed or power change.
• 7. The WWKM technique will be completed after its successful Development phase predestined be as a prime mover for Power plants, ships or locomotives to be used. she will there a significant contribution to the improvement of these facilities especially with regard to the economic and ecological Operate.
• 8. According to today's assessment An overall efficiency of the WWKM technique appears on the order of magnitude of about 70% as possible.

Significant efficiency losses in diesel and gasoline engines:

• 1. Energy loss through heat dissipation, for self-protection of the engine, necessary cooling around the combustion chamber, loss about 32%
• 2. Energy loss through propellant gas emissions with very high unused Temperature, loss about 29%
• 3. Energy loss through heat radiation of the engine block, loss approx. 7%
• 4. Energy loss due to poor force or torque conversion as a result of unfavorable Crankshaft position. This means, at the time of the largest power generation (ignition timing = approx. top dead center of the crankshaft) is the lever arm (effective radius) approximating the crankshaft = 0. In the course of the following rotation angle change is simultaneously the Effective radius larger and the force of the piston due to the expansion of the propellant gas smaller.
• 5. Energy loss due to poor utilization of expansion work. Because the length the expansion stroke equal to the length is the previous compression stroke, only the Exponentially expand volume that was previously compressed. Due to the interim fuel combustion, however, has the former intake or compression volume increased considerably and thus significantly increasing the pressure. The expansion stroke can be due to the design of the now much larger propellant gas volume beneficial only up to the volume size of the previous intake volume be expanded, whereby the remaining, residual pressure, Propellant gas volume must be derived useless.

23 and 24 illustrate in particular an expansion machine according to claims 34 to 37. In particular, the piston 914 ' according to the 23 and 24 can be significantly slimmer in the practical embodiment, in particular be designed with a significantly reduced diameter. The same applies to the piston rod 930 ' to. In addition, reference numerals denote the 23 . 24 and 9 similar elements, but in the specific embodiment may differ from each other.

The general operation of the expansion machine according to 23 results from the description of the expansion machine according to 9 to which reference is hereby made. In particular, deviations are explained below. The expansion machine according to 23 is not intended to be used in the pressure room 925 ' Process gas, in particular air to compress, but using propellant gas the movement of the pistons 914 ' or the piston rod 930 ' to support. The compression of required compressor air must thus be performed elsewhere, such as by a separate or separately operated compressor. Also a coupling over the sprockets 932 , such as in 13 shown in another embodiment, comes into consideration.

23 shows the expansion machine in a state in which the pistons 914 ' and thus the piston rod 930 ' to move to one side, namely according to 23 to the right. The direction designations used on the right or left refer to the present view of the 23 ,

Propellant gas in the left propellant gas expansion space 928 expands and pushes against the first pressure surface 981 and thereby moves the piston 914 ' to the right. In the right pressure chamber 925 ' There is also propellant gas flowing through the controlled valve 962 ' was admitted. This propellant gas presses against the second pressure surface 982 the piston unit shown on the right 991 and thereby also leads to a rightward movement of the right piston 914 ' , The effect of the propellant gas in the propellant gas expansion space 928 the left piston unit 992 and the action of the propellant gas in the pressure space 925 ' the right piston unit 991 complement each other and lead both to a rightward movement of the two pistons 914 ' and the piston rod 930 ' ,

At the same time, propellant escapes from the propellant gas expansion space 928 the right piston unit 991 by the controlled and opened as shown valve 908 , The effluent propellant heats water in the heat exchanger 970 , At the same time propellant gas flows out of the pressure chamber 925 ' the left piston unit 992 through the controlled valve 958 ' off and becomes the heat exchanger 970 guided.

Once the pistons 914 ' and the piston rod 930 ' arrived at their right reversing position, close the valves 908 and 958 ' , The valve 912 the right piston unit 991 opens, so that propellant gas into the propellant gas expansion chamber 928 flows and the piston 914 ' pushes to the left. At the same time propellant gas through the control valve 962 ' the left piston unit 992 in the pressure room 925 ' The left piston unit is inserted and thus leads by a pressure on the second pressure surface 982 this left piston unit to a movement of the piston 914 ' and the piston rod 930 ' to the left. After the pistons 914 ' and the piston rod 930 ' have moved to a part to their left reversal point, becomes the controllable valve 912 the right piston unit 991 as well as the control valve 962 ' the left piston unit 992 closed. Now only the expansion of the propellant gas in the propellant gas expansion space leads 928 the right piston unit 991 and in the pressure room 925 ' the left piston unit 992 to a force on the pistons 914 ' in the direction of movement. The controlled valves 908 the left piston unit 992 and 958 ' the right-hand piston unit are open and propellant gas can flow out and water in the respective heat exchanger 970 heat.

The expansion machine according to 24 is essentially prepared to, either as the expansion machine according to 23 to be served - this possibility is according to 24 shown as selected - or according to 9 to be operated and simultaneously perform a compressor function. For this purpose, at the entrance of each controlled valve 962 ' a changeover valve 984 provided that the valve 962 ' and thus the pressure room 925 ' either propellant gas - as shown - or optionally air supplies. Accordingly, the controlled output valve 958 ' a changeover valve 986 downstream, the use of propellant gas in the pressure chamber 925 ' this to the respective heat exchanger 970 conducts - as shown - or when using air after compression in the pressure chamber 925 ' to the compressor air block 988 leads, so that there is compressor air available.

According to one embodiment, different expansion machines, in particular expansion machines according to 9 . 23 and or 24 be mechanically coupled, for example, to a common shaft. Will an expansion machine as related to 23 used, it is usually advantageous to the pistons 914 ' in their diameter as thin as possible, so that the pressure surfaces 982 and 981 about the same size.

Claims (49)

Propellant gas generating device for generating a Pressurized propellant gas for performing mechanical work, comprising: - one LPG pressure vessels for generating the propellant gas therein, - a combustion chamber with a Burner for burning a fuel to produce a fuel gas, wherein the combustion chamber is so connected to the LPG pressure vessel is that the fuel gas enters the propellant pressure vessel and - a secondary fuel supply for introducing secondary fuel, in particular water in the LPG pressure vessel for cooling the fuel gas. Propellant gas generating device according to claim 1, characterized characterized in that the combustion chamber is arranged in the LPG pressure vessel or forms part of the propellant pressure vessel. Propellant gas generating device according to one of the preceding Claims, characterized in that the combustion chamber with burner - a fuel supply for feeding of fuel and - one Air supply for feeding of air and the burner is prepared for mixing, in particular, swirling the air and fuel and starting a combustion in the combustion chamber, and the propellant gas generating device has optionally an air compressor for generating compressed air for providing the compressed air at the air supply or a connection to a compressed air supply on, and optionally an air flow control valve for controlling the pressure and / or the amount of compressed air provided. Propellant gas generating device according to one of the preceding claims, further comprising a fuel pump and / or a fuel compressor to fuel the combustion chamber and / or in particular to supply the burner under pressure, and optionally a fuel quantity control valve for controlling the amount of fuel to be supplied. Propellant gas generating device according to one of the preceding claims further comprising a secondary fuel pump, in particular a water pump to the secondary fuel, in particular water at the secondary fuel supply to provide under pressure for introduction into the propellant pressure vessel under Pressure and optionally a control valve for secondary fuel, in particular a Water quantity control valve for controlling the secondary fuel supplied or amount of water. Propellant gas generating device according to one of the preceding Claims, further comprising a control unit for controlling the propellant gas generating device, in particular the fuel supply, the air supply and / or the secondary fuel supply. Propellant gas generating device according to one of the preceding Claims, characterized in that a secondary fuel line is provided for conducting the secondary fuel to the secondary fuel feed, the along at least one wall of the propellant pressure vessel extends to a warm up of the secondary fuel by heat of LPG pressure vessel to reach. Propellant gas generating device according to one of the preceding Claims, characterized in that the propellant pressure vessel at least Sectionally executed at least double-walled and between two walls of the secondary fuel and / or the air for feeding to the LPG pressure vessel or the combustion chamber out becomes. Propellant gas generating device according to one of the preceding Claims, further comprising a second secondary fuel supply for supplying another Secondary fuel. Propellant gas generating device according to one of the preceding Claims, further comprising a heat exchanger for heating at least one secondary fuel from heat of the propellant and / or heat another medium. Method for generating a propellant gas under pressure for performing mechanical work using a propellant gas generator with a propellant pressure vessel, one with the propellant pressure vessel connected combustion chamber and a secondary fuel supply for introduction of secondary fuel in the propellant pressure vessel, comprising the steps - Burn a fuel in the combustion chamber for generating a fuel gas, - Conduct of the fuel gas in the propellant pressure vessel and - Initiate of secondary fuel, in particular water in the LPG pressure vessel for cooling the fuel gas, around thereby to generate the propellant gas in the propellant pressure vessel under pressure. Method according to claim 11, characterized in that in that a propellant gas generating device according to one of claims 1 to 10 is used. Method according to claim 11 or 12, characterized that - the Burning the fuel to the fuel gas with the supply of Air is done, - when Secondary Fuel Water in liquid Form so fed is that it evaporates when mixing with the fuel gas and so on an increase in volume of the Water leads or is already supplied as water vapor and / or - the propellant Fuel gas and water vapor and / or at least one secondary fuel has, in particular a mixture of fuel gas and water vapor and / or at least one secondary fuel is. Method according to one of claims 11 to 13, characterized that the combustion is under pressure takes place. Method according to one of claims 11 to 14, characterized that the combustion chamber provides compressed air through a compressed air compressor is optional under additional Using a compressed air control valve, and the pressure and / or quantity the compressed air is controlled. Method according to one of claims 11 to 15, characterized that the combustion chamber and / or the burner fuel by means of a fuel pump and / or a fuel compressor, optionally using a Fuel quantity control valve, in particular under pressure, and wherein the to be supplied Fuel quantity is controlled. Method according to one of claims 11 to 16, characterized that the propellant pressure vessel Water by means of a water pump and optionally using a Water control valve is supplied under pressure and the amount of water supplied is controlled. Method according to one of claims 11 to 17, characterized that as fuel a flowable fuel is used, in particular gas, oil, gasoline and diesel. Method according to one of claims 11 to 18, characterized in that the preheated as secondary fuel water is used and / or water is misted into the propellant pressure vessel under pressure. Method according to one of claims 11 to 19, characterized that the secondary fuel supply, the fuel supply and / or the compressed air supply depends on Measurements of states takes place in the propellant gas generating device, in particular depending on Measurements of temperature, volume, pressure and / or composition of the propellant and / or dependent from the temperature in the burner takes place and / or a control of proportions and / or the pressure of the compressed air, the fuel and the water he follows. Method according to one of claims 11 to 20, characterized the method is controlled so that the propellant gas approximately the propellant pressure vessel with a pressure of 10 to 50 bar and a temperature in the range from 750 ° C up to 1200 ° C leaves. Expansion machine for converting in propellant under Pressure energy contained in a mechanical movement, in particular Rotary movement, comprising a first expansion part arrangement comprising: - one filling space for filling with the propellant, in which a moving body with a first pressure surface movable guided is going to change of the filling space in size and to Converting a motion or expanding the propellant into a motion of the moving body with a first direction and - a propellant gas expansion space for feeding of propellant in which the moving body is movable with a second pressure surface guided is to change of propellant expansion space in size and to transform an expansion of the propellant gas in a movement of the moving body with a second direction and - in which the first and second printing surfaces are arranged to each other so that an enlargement of the filling space leads to a reduction of the propellant gas expansion space. Expansion machine according to claim 22, characterized in that that the first printing area is smaller is as the second printing surface. Expansion machine according to claim 22 or 23, characterized marked that - of the filling space is designed as a cylinder space or annular gap and the first pressure surface as Circle or ring surface is trained, - Moving body as Piston executed is and / or - of the Treibgasexpansionsraum formed as an annular gap or cylinder space is and the second printing surface as ring or circle surface is trained. Expansion machine according to one of claims 22 to 24, characterized in that the filling space and the Treibzasxpansionsraum overlap, are formed in particular in a common bore. Expansion machine according to one of claims 22 to 25, comprising - at least one with the first filling space functionally connected filling valve for introducing propellant gas into the first filling space, - at least an outlet valve operatively connected to the propellant gas expansion space for discharging propellant gas from the propellant gas expansion space and / or - at least one with the filling room and the propellant gas expansion space functionally connected overflow valve to open and closing a connection between the filling space and the propellant gas expansion space to allow propellant gas from the filling room to flow to the propellant gas expansion space. Expansion machine for converting an expansion of Propellant gas under pressure in a mechanical movement, in particular Rotary movement, with a first expansion part assembly to the functional Connecting to a propellant gas generating device comprising: - one Propellant gas expansion space for filling with propellant, in which a moving body with a pressure surface movable guided is used to modify the Propellant expansion space in size and transforming an expansion of the propellant in a translational movement of the moving body with a first direction, - one Compression space in which the moving body with a compression surface movable guided for compressing a process gas received therein, in particular Air, by a translational movement of the moving body in the first direction, and - one with the moving body connected conversion mechanism for converting the translational movement of the moving body in a rotary motion. The expansion machine of claim 27, wherein the pressure area is larger as the compression surface, and / or the printing surface as a circular area and the compression surface as a ring surface are formed with the same outer diameter, in particular, that a cylinder space is provided, in which the Treibgasexpansionsraum and the compression space are formed. Expansion machine after one of the Claims 22 to 28, characterized in that the first expansion part assembly is coupled to a second expansion part assembly having the same features, wherein the moving body of the expansion part assembly are united to a common moving body, and are coupled in opposite directions, that in the Treibgasexpansionskammer the first expansion subassembly a propellant gas expand, while the propellant gas expansion chamber of the second expansion subassembly escapes a propellant gas at reduced pressure. Expansion machine according to one of claims 22 to 29, comprising a flywheel for storing and dispensing a Kinetic energy from or to the moving body. Expansion machine according to one of claims 22 to 30, characterized in that the or a conversion mechanism at least one rack connected to the moving body and at least one gear means coupled to the rack comprises for converting a translational movement of the rack in a rotational movement on the gear means. Expansion machine according to claim 31, characterized in that that the conversion mechanism at least A first gear means has a translatory movement of a first direction of the moving body to convert into a rotational movement with a first direction of rotation and - a second Gear means to a translational movement of a second Direction of the motor body to turn into a rotational movement with the first direction of rotation, in which the expansion machine, in particular the conversion mechanism to is prepared between the first and second gear means so to switch over that an oscillating motion of the moving body in a rotational movement is converted with the first rotational direction, and / or wherein each gear means a freewheel, in particular a controlled Clutch freewheel, in each case only at the first or the second direction of the translational movement to be effective. Expansion machine according to one of claims 22 to 32, comprising an expansion machine control unit for controlling the expansion machine, in particular for controlling valves and / or the conversion mechanics. Expansion machine for converting an expansion of Propellant gas under pressure in a mechanical movement, in particular Rotary movement, with a first expansion part assembly to the functional Connecting with a propellant gas generating device comprising - at least a piston unit with: - one first Treibgasexpansionsraum for filling with propellant, in which moving body with a first printing surface movably guided is going to change of propellant expansion space in size and to convert an expansion of the propellant in a translational movement of the moving body with a first direction and - one Pressure chamber in which the moving body with a second printing surface movably guided is for compressing a process gas received therein, in particular Air, by a translatory movement of the moving body in the first direction or filling with propellant to change of the pressure chamber in size and to Converting an expansion of the propellant gas in a translational movement of the moving body with a second direction that opposes the first direction is and - at least one with the moving body connected conversion mechanism for converting the translational movement of the moving body in a rotary movement or to forward the translational movement. An expansion machine according to claim 34, comprising at least a first and a second piston unit, wherein the moving bodies in opposite directions mechanically are coupled. An expansion machine according to claim 35, wherein both moving body are so coupled, in particular rigidly coupled, that the first Direction of movement of the first piston unit of the second direction of movement corresponds to the second piston unit. Expansion machine according to one of claims 34 to 36, wherein each piston unit is a valve switching unit for optional Respectively of process gas, in particular air, or propellant gas to the pressure chamber. Expansion machine according to one of claims 22 to 37, characterized in that at least one or at least one with the moving body connected conversion mechanism for converting the translational movement of the moving body in a rotary motion has a flywheel for storing Rotational energy, wherein the at least one flywheel preferably forms a rotor of a generator. Arrangement of at least two expansion machines according to any one of claims 22 to 38, wherein the expansion machines are coupled so that they each conduct a torque to a common shaft, in particular the expansion machines are prepared to be synchronized and / or coordinated. Method for operating an expansion machine includes the following with a first expansion subassembly a filling room and a propellant expansion space directed steps in order the listing: Step 1: Fill a filling space over at least one filling valve with propellant, so that the pressure of the propellant gas on a first pressure surface at one moving body acts and thereby increases the filling space and the moving body is moved in a first direction, Step 2: Close the at least one filling valve and, possibly with a time delay, open at least one overflow valve, so that the propellant gas from the filling space flows into a propellant gas expansion space and there to a second print area to the moving body acts and thereby increases the propellant gas expansion space and the moving body in a second direction is moved, wherein the second direction to the opposite to the first direction, Step 3: Open at least an exhaust valve to the propellant gas from the Treibzasxpansionsraum to let escape Step 4: Repeat the procedure starting with step 1. Method for operating an expansion machine includes the following with a first expansion subassembly directed to a propellant gas expansion space and a compression space Steps in the order of listing: Step 1: Fill the Propellant gas expansion chamber with propellant gas, so that the pressure of the propellant gas on a printing surface on a moving body acts and thereby increases the propellant gas expansion space and the movement body is moved in a first direction, whereby a process gas in the Compression space is compressed, Step 2: Move back of the moving body in the second direction, thereby emptying the Treibgasexpansionsraums and filling the compression chamber with process gas and Step 3: Repeat from step 1. Method according to claim 41, characterized that two expansion sub-assemblies coupled with the same features operated, with their directions of movement directed opposite are, with the two expansion sub-assemblies are operated so that their movements complement each other and they have a common moving body. Heat engine for generating a mechanical movement using a fuel, full - one Propellant gas generating means for generating a propellant gas one of the claims 1 to 10 and - one Expansion machine for converting an expansion of propellant gas under Pressure in a mechanical movement, in particular rotational movement after a the claims 22 to 38, wherein the propellant gas generating means and the expansion machine are coupled to each other, that of the propellant gas generating device generated propellant gas is supplied to the expansion machine, in particular at least one or the at least one filling valve or an inlet valve a propellant gas expansion chamber is provided. Heat engine according to claim 43, characterized in that the expansion machine leaving propellant gas is fed to a or the heat exchanger, at least one secondary fuel to warm up. A method of operating a heat engine, comprising the steps: - Produce a propellant gas under pressure using a propellant gas generator according to one of the claims 1 to 10 and / or using a method according to one of claims 11 to 21, - Change the propellant gas under pressure in a mechanical movement, in particular a rotational movement using an expansion machine after one of the claims 22 to 38 and / or using a method according to one of claims 40 to 42. Compressor for compressing a process gas, in particular comprising air: - a first compression room with a first compression body movable therein for compressing a Process gas, in particular air and - a second compression space with a second compression body of the same arranged movably relative thereto Process gas, wherein the second compression space is formed in the first compression body is. A compressor according to claim 46, characterized in that - the first compression space is prepared to compress the process gas in a first compression stage to a volume with a first compression pressure, - at least one connection valve is provided to compressed process gas of the first compression stage in the second compression space and - the second compression space is prepared to process gas from the first compression stage to a volume in a second compression stage to compress with a second compression pressure. Compressor according to claim 46 or 47, characterized that the first compression space and the second compression body to each other arranged are the first compression body to the first compression space and the second compression body so arranged in two directions that is movable from his Move either a reduction of the first compression space and an enlargement of the second compression space results, or an increase in the first compression space and a reduction of the second compression space results. Steam generator for generating water vapor from water full: - one preheating to preheat of the water, - one Evaporation area for evaporation of water and - a heat source for heating the preheating area and the evaporation area, the steam generator to do so is prepared, preheated Water from the preheat area via propellant injection nozzles in the Inject evaporation area so that the water in the evaporation area evaporated to steam, the heat source preferably to is prepared to provide and / or generate a heating medium, the first is passed to the evaporation area to heat it and from there to the preheating area is passed to heat this.