WO2019201969A1 - Device for driving a generator - Google Patents

Abstract

The invention relates to a device for driving a generator (3) for generating electrical energy, said device comprising a rotor (10) that is rotatably mounted about an axis of rotation (5), wherein a plurality of rocket engines (14) having combustion chambers that are open on one side are circumferentially arranged on the rotor (10) at a radial distance (D) from the axis of rotation and are rigidly connected to the rotor (10) in order to rotate about the axis of rotation in an operational state of the device, thus rotationally driving the rotor (10) about the axis of rotation. It is provided according to the invention that the structure of the rotor (10) comprises carbon fibers in a heat-resistant and pressure-resistant matrix, preferably of silicon carbide, wherein more than 50% of the carbon fibers are arranged in such a way that the respective carbon fiber extends transversely to a tangent, wherein the tangent extends through a point on the respective carbon fiber, and in said point tangentially touches an auxiliary circuit that centers about the axis of rotation, is arranged in a plane that is normal to the axis of rotation, and extends through the point.

Description

 DEVICE FOR DRIVING A GENERATOR

FIELD OF THE INVENTION

Device for driving a generator for generating

electrical energy, the device comprising a rotor rotatably mounted about a rotation axis, wherein on the rotor at a radial distance from the axis of rotation a plurality of rocket engines circumferentially arranged on one side combustion chambers and rigidly connected to the rotor to rotate in an operating state of the device about the axis of rotation and thus to rotatably drive the rotor about the axis of rotation, wherein the combustion chambers are preferably designed as expansion nozzles.

STATE OF THE ART

The energy conversion efficiency of solid fuels is far behind that of liquids or gases. Especially because of the large installed capacity of coal power plants, this is unsatisfactory.

In the conversion of thermal energy into mechanical energy, in particular in connection with power generation by

Combustion in a Carnot process is the achievable

Efficiency by the ratio of maximum

Operating temperature determined to waste heat temperature. Therefore, technical efforts are trying, above all, to maximize the working temperature, for example in a gas turbine. Especially at However, the combustion of impure solids occur

Corrosive effects on the reliable use

prevent efficient conversion processes.

From the prior art, cf. e.g. D.R. Hardy et al. .

ADVANCED MATERIALS & PROCESSES / APRIL 2007 p 30ff: "POWERING THE FUTURE, ADVANCED COAL COMBUSTION TECHNOLOGIES", the following approaches are known, especially with regard to coal as an energy carrier:

One attempt at solution is to filter the hot exhaust gases of a high-pressure combustion in a heat-resistant filter, for example made of ceramic, of corrosive particles and then to supply them to an expansion turbine.

However, filter materials that have grown reliably and permanently to meet the extreme requirements are not easy to find.

Operation of a gas turbine with pulverized coal is practically not possible in the long term, since the coal combustion produces ash which would quickly destroy the blades of the gas turbine by abrasion. The ash would therefore have to be separated from the hot gas stream. On finding one

Large-scale solution to this problem is currently being worked on. Therefore, another known approach is to convert the solid fuel into a combustible gaseous form in a first step (e.g.

Hydrogen and carbon monoxide) and then burn them in a gas turbine. The cleaning process takes place in the gasification phase. However, here too no complete purification of impurities such as e.g. from

Sulfur and other pollutants. It should be noted that the heat produced by the combustion in the gas turbine exhaust gas can be used to increase efficiency for the production of steam and thus to drive a steam turbine, which is also referred to as gas and steam process (CCGT) process. One of the disadvantages of all of these approaches is the limited scalability of the electrical power generated

Power .

EP 3085922 A1 discloses a device for converting thermal energy into mechanical or electrical energy, comprising a shaft and jet engines, wherein the

Jet engines have combustion chambers and in one

Operating state Rotate supporting arms in rotation.

OBJECT OF THE INVENTION

The aim of the present invention is to provide a device for power generation which avoids the above-mentioned disadvantages and in particular a good one

Scalability and achieving high efficiencies in the use of solid fuels allowed.

PRESENTATION OF THE INVENTION

The core of the invention is to provide as a thermodynamic machine, a set of small rocket engines mounted on a high-strength rotor about a common axis of rotation

circling. By means of such a device, in turn, a generator can be driven, wherein the conversion of the generated electrical energy to the mains frequency in a conventional manner electronically. The rocket engines are active burners whose power is e.g. 1 MW, whereby the complexity of the system comparatively low and the performance - in contrast to known solutions - is well scalable. The division on a variety of

Rocket engines or burners also has great advantages for system availability. Accordingly, it is in a device for driving a generator for generating electrical energy, the device comprising a rotor rotatably mounted about an axis of rotation, provided that at the rotor at a radial distance from the axis of rotation more

 Rocket engines are arranged circumferentially with one side open combustion chambers and rigidly connected to the rotor to rotate in an operating state of the device about the axis of rotation and thus rotatably drive the rotor about the axis of rotation, the combustion chambers preferably as expansion nozzles

are formed.

The openings of the combustion chambers are arranged so that the support mass is substantially tangential to the rotor or to

Course of an imaginary circle whose radius is the radial distance and which is centered about the axis of rotation

is ejected. The rocket engines are attacking

Essentially tangential to the imaginary circle on the rotor and can thus achieve an angular acceleration of the rotor or set a speed of the rotor. Correspondingly, the "rotary" drive means that in the operating state, a rotation of the rotor about the axis of rotation is effected by the rocket engines. "Essentially tangential" is to be understood that the rocket engines with a tangent to the imaginary circle a small angle, preferably from 0 ° to 5 °, so that the exhaust jet or support mass is directed more away from the rotor to

Damage to the rotor by the exhaust gases to avoid.

Preferably, the distribution of rocket engines along the imaginary circle is regular - i. in a regular sequence of angular intervals -, in particular in the same

Angular distances.

Expansion nozzles are known per se and are also referred to as Laval nozzles.

In order to minimize the mass in the periphery of the rotor while guaranteeing a high strength of the rotor, it is provided in the inventive device that the structure of the rotor carbon fibers in a heat and

pressure-resistant matrix, preferably of silicon carbide, wherein more than 50%, preferably more than 66%, of the carbon fibers are arranged so that the respective carbon fiber runs transversely to a tangent, the tangent passing through a point on the respective carbon fiber and in FIG this point touches an auxiliary circle tangentially, which auxiliary circle is centered about the axis of rotation and arranged in a plane perpendicular to the axis of rotation and extends through the point. In particular, the point may be any point on the particular carbon fiber.

The low mass in the periphery of the rotor causes a low moment of inertia and allows correspondingly high angular acceleration at relatively low

Energy. More importantly, the centrifugal forces caused by the peripheral mass, which cause the

Claim material of the rotor, can be kept as small as possible.

Not only does silicon carbide as a matrix withstand the increased temperatures encountered in rocket engine operation, it also advantageously has a high temperature

Corrosion resistance on, which is beneficial to the

Stability and reliability of the device according to the invention affects.

By having the majority of carbon fibers across

runs corresponding tangent, the carbon fibers are largely at least roughly parallel to the occurring

Centrifugal forces. That is, the carbon fibers are arranged so that they are loaded in the operating state, at least roughly parallel to the direction in which they have their maximum strength, which the strength of the rotor in terms of enormously increases loads occurring in the operating state due to the centrifugal forces.

In order to increase the strength of the rotor still further, it is in a particularly preferred embodiment of the

Device according to the invention provided that the course of the respective carbon fiber with the tangent an angle of 55 ° to 90 °, preferably from 65 ° to 90 °, includes.

In particular, the carbon fibers can thus extend radially (to the axis of rotation or away from it), in which case said angle is 90 °.

In a preferred embodiment of the device according to the invention it is provided that an outer radial

Section of the rotor, in which the rocket engines are arranged, is arranged in an exhaust space, as seen from the outer radial portion of the rotor to the rotational axis, a housing, the exhaust gas chamber gas-tight, and that between the housing and the axis of rotation, a working space is arranged, in which an inner radial portion of the rotor is disposed, and wherein the working space is evacuated to in

Operating state of the device to allow the arrangement of the inner radial portion of the rotor in vacuum.

That the housing limits the working space opposite the

Exhaust gas chamber gas-tight, so that the working space can be evacuated.

Preferably, the exhaust space is formed substantially closed, with means for discharging the exhaust gases are provided.

The terms "evacuable" and "vacuum" are clearly to be understood to mean such vacuums that can be technically easily implemented in practice. To ensure this vacuum in the working space, the inner radial section of the rotor can be sealed off from the exhaust gas chamber, for example by means of a non-contact seal, which is arranged in the region of the housing and, for example, completely analogous to a rotor of an evacuation pump

can be designed. In addition, a gas curtain known per se may be provided in the non-contact seal.

According to the arrangement of the working space, the inner radial portion of the rotor is disposed between the outer radial portion of the rotor and the axis of rotation.

By moving with the inner radial portion of the rotor, a substantial part of the existing mechanics in a vacuum, surfaces which are exposed to the rapidly moving exhaust gases of the rocket engines, minimized, which in turn advantageous to the stability of the

inventive device effects.

In a preferred embodiment of the device according to the invention it is provided that in the operating state of the rotor can be driven at an operating speed, in a

Range from 9000 min ^-1 to 36000 min ^-1 , preferably from 16000 min ^-1 to 24000 min ^-1 , and is preferably an integer multiple of a frequency of a low-voltage power network.

In Europe, low-voltage power grids are usually used which provide 230 V single-phase or 400 V three-phase with 50 Hz mains frequency. In some countries of the world, e.g. also 60 Hz used as mains frequency.

The speed is high and preferably an integer

Many times the mains frequency, eg 18000 min ^-1 . For conversion into an AC voltage usable in the low-voltage power network, a wide variety of known means can be used.

For example, a known, electronically operating frequency converter can be used, which can be co-optimized in particular with the generator.

Alternatively or additionally, for example, a mechanical solution would also be conceivable in which a transmission, e.g. one

Planetary gear with a rigid gear ratio, is connected between the generator and the device or the rotor according to the invention. In operation, mechanical wear must be taken into account, e.g. by usual maintenance and inspection measures.

Another variant for the conversion in im

 Low voltage power grid usable AC voltage would be e.g. the use of a generator with counter rotating field in the rotor. For example, if the rotor of the generator rotates at 6 times the mains frequency, but at the same time the rotor generates a field of excitation with 5 times the mains frequency in the opposite direction, the mains frequency will also be in the opposite direction

Stator windings generated so that not all the electrical power generated must be electronically transformed, but the electronics only has to muster the power of the exciter field.

By said operating speed can be achieved that the peripheral speed - ie the tangential velocity of the expansion nozzle or the rocket engine in the above

said radial distance or radius - about the

Gas velocity corresponds, so that the energy output is maximized in a single-stage expansion process, for example, 1500 m / s. A possible parameter combination is for example a speed of 18000 min ^-1 and a radius of 0.8 m. In this case, a centrifugal acceleration of about 290000 g occurs. The centrifugal force occurring in the operating state or centrifugal force can advantageously be used to supply fuel to the rocket engines.

Problems transporting the fuel into the combustion chamber against a prevailing pressure, such as this

conventional liquid missile engines frequently

can be avoided in this way. Furthermore, the high pressure used in the initiation of combustion, which is generated by the rotation itself without additional aggregates, the additional advantage that low-frequency

 Combustion instabilities are suppressed. Accordingly, it is in a preferred embodiment of

Inventive device provided that in the region of the axis of rotation a fixed supply line for fuel

is provided, which opens into at least one fuel line, wherein the at least one fuel line is rigidly connected to the rotor and preferably in the rotor

is formed, wherein the at least one

Fuel line radially up to the rocket engines

extends to press in the operating state, the fuel by means of the present by the rotation of the rotor centrifugal force in the rocket engines. The rotor turns

relative to the fixed supply line in the operating state.

Accordingly, the fuel line in a spatial mouth region, in which the supply line in the

Fuel line opens, e.g. as annular or

circular, in each case centered around the axis of rotation, be executed recess in order to take into account the relative movement between the supply line and the rotor or fuel line.

According to the above is preferably also the

Mouth area in the work area - and thus in the operating state in a vacuum - arranged. A substantially gas-tight or vacuum-tight seal of the fuel line in

Mouth area opposite the working space can, for example, analogous to above-explained gas-tight seal of the evacuated

Working space opposite the exhaust gas space by means of a

contactless seal done.

In a particularly preferred embodiment of the

Device according to the invention is provided that the

Each combustion chamber is designed as an expansion nozzle with a pre-combustion chamber and an adjoining main combustion chamber, wherein a light cross-section of the expansion nozzle

between the pre-combustion chamber and the main combustion chamber has a constriction, wherein the at least one

Fuel line merges into a fuel supply end portion, which opens into the pre-combustion chamber.

Simplified it can be said that in the main combustion chamber the actual, as complete as possible combustion

takes place while in the pre-combustion chamber a

Partial combustion takes place, which raises the temperature level to reduce the ignition delay time. The constriction between the pre-combustion chamber and the main combustion chamber prevents vortices that would contact hot particles with an inner wall of the expansion nozzle in this area and would promote corrosion.

Since it is an expansion nozzle, an expansion area connects to the main combustion chamber. Basically, in known expansion or Laval nozzles, the clear cross section of the main combustion chamber to the adjoining expansion area so that the clear cross section in a transition between the main combustion chamber and the

Rejuvenated expansion area and then in the expansion area relatively strong increases. This course of light

Cross-section, which is known in expansion or Laval nozzles, ensures that a discharged from the expansion nozzle fluid, which forms the support mass, flows as parallel as possible to a longitudinal axis of the expansion nozzle and that sudden changes in the flow state, so-called.

Compression collisions, be avoided when using the fluid

Supersonic velocity flows.

In the device according to the invention it can be provided that, although not tapering in the region of the transition, the light cross-section is not extended to collisions of ash particles with an inner wall of the expansion nozzle in the

To avoid the area of transition. The function of

Rejuvenation of the clear cross section in the region of the transition can then still - be realized in fluid form by at least one fluid, preferably gas, particularly preferably nitrogen-enriched fluid or gas, in the region of the transition under relatively high pressure to the center of the clear cross section is passed, so that forms a fluid flow, the function of the rejuvenation of the clear

Cross section fulfilled.

Accordingly, in the device according to the invention or in its rocket engines optimal conversion of the heat energy generated by the combustion of the fuel in kinetic energy is achieved. This implementation is going through

Relaxation of the fluid in the so-called expansion region of the expansion nozzle or the main combustion chamber instead.

In order to achieve optimal combustion, the use of an oxidizer is provided, oxygen or oxygen-enriched air in particular being able to be provided as the oxidizer. The oxygen or the oxygen-enriched air can be present in liquefied form or in

gaseous form, so at least as a fluid. It should be noted that the gaseous oxidizer is due to in operation

prevailing high pressures can have a density which is almost as large as a liquid oxidizer.

Furthermore, by the use of the oxidizer the

Nitrogen oxide production during combustion reduced or minimized. According to the invention, in turn

Operating state occurring centrifugal advantageous to be exploited to the oxidizer rocket engines

supply. Accordingly, it is at a special

preferred embodiment of the device according to the invention provided that at least one Oxidatorleitung is provided, which is rigidly connected to the rotor and is preferably formed in the rotor, wherein the at least one

Oxidator at least partially radially extends up to the rocket engines to press in the operating state, an oxidizer by means of the present by the rotation of the rotor centrifugal force in the rocket engines. That it may be dispensed with additional, known from the prior art, facilities to the oxidizer in the

Press rocket engines.

The achievable high pressures of the oxidizer can also be used to decompose the fuel into very small particles or droplets. For this purpose, it is in a particularly preferred embodiment of the

Device according to the invention provided that in each case in the pre-combustion chamber in the region of the constriction more openings are provided for the oxidizer, in which openings

Oxidator supply end sections open, the

 Oxidatorzufuhrendabschnitte and the openings are designed such that in the operating state, the oxidizer at a pressure of at least 1500 bar, preferably from 2000 to 6000 bar, more preferably from 2500 bar to 5000 bar, can be introduced in the direction of the constriction in the pre-combustion chamber to the

To crush fuel in the area of the constriction.

The oxidator is thus at high pressure in the region of the constriction, so to speak, from several sides in a

Injected in the area of the constriction and cuts in this area due to the high pressure fuel - similar or analogous to a water jet Cutting machine. The said narrowing between

Pre-combustion chamber and main combustion chamber serves as it were as a guide for the radial or the center of the clear

Cross-section oxidizer feed.

The diameter of the thus comminuted fuel particles or droplets is typically less than or equal to 10 ym.

In order to achieve said injection into the central area of several pages, the course of the

 Oxidatorzufuhrendabschnitte substantially star-shaped and preferably aligned with the central region. In other words, the course of the Oxidatorzufuhrendabschnitte is preferably pointing to a longitudinal axis of the expansion nozzle, which longitudinal axis lies in a plane of the rotor or in a plane normal to the rotation axis and is substantially tangential (to the rotor), and run

Oxidatorzufuhrendabschnitte pointing to an opening direction of the expansion nozzle or to the one-sided opening of the respective combustion chamber.

The achieved small particle size of the fuel contributes to an enormous efficiency increase of the combustion.

In particular, this applies to solid fuels, such as e.g. Coal too. The coal can be in the form of larger grains, which

typically have diameters in the range of 50 ym to 1 mm, are transported into the pre-combustion chamber. The supply of coal grains by means of a fluid is not absolutely necessary, but may possibly be provided.

In a particularly preferred embodiment of the

Device according to the invention is provided that the

at least one Oxidatorleitung in Oxidatorringleitungen opens, each extending annularly around one of the rocket engines in the region of a transition from the main combustion chamber to an expansion region of the expansion nozzle, and that the Oxidatorringleitungen each in channels in a wall of the respective expansion nozzle open, which channels extend from the region of the transition in the region of the constriction of the respective expansion nozzle. This arrangement is advantageous in two respects. For one thing, the

Oxidizer in the Oxidatorringleitungen and channels regeneratively warmed, resulting in a better combustion result. On the other hand, the main combustion chamber is cooled by the oxidizer, whereby the combustion chamber material, in particular the material of the main combustion chamber, is protected from oxidation.

To minimize corrosion and abrasion of the combustion chambers or combustion chambers, it is provided in a preferred embodiment of the device according to the invention that the combustion chambers are formed of a temperature-resistant alloy with oxidation-resistant material and a ceramic coating

exhibit. As the ceramic coating, in particular, a hard oxide ceramic such as e.g. Al O (alumina), in question.

As the temperature resistant alloy, e.g. a

Superalloy, such as IN909, to be used. The

Ceramic coating is biased by a sheath of the superalloy to pressure.

In order to be able to ensure the supply of oxidizer, it is provided in a preferred embodiment of the device according to the invention, that an air _Z erlegungseinheit is provided to liquefied air in a

decompose nitrogen-rich fraction and an oxygen-rich fraction and the oxygen-rich fraction as oxidizer

to be able to use.

As already mentioned, when used as an oxidizer, the oxygen-rich fraction no longer has to be in liquid form

but may also be gaseous. The same applies to the nitrogen-rich fraction. That is, after the air _Z in this case, the oxidizer and / or the

nitrogen-rich fraction in gaseous form. In a particularly preferred embodiment of the device according to the invention it is provided that the

Air _Z erlegungseinheit a about the rotation axis rotatable, rigidly connected to the rotor vessel for the liquefied air comprises, in which vessel in the operating condition by rotating a pressure gradient can be formed in the liquefied air to produce the oxygen-rich fraction as by means of fractional crystallization, that the oxygen-rich fraction in the vessel is arranged radially further away from the axis of rotation than the nitrogen-rich fraction, and that at least one

Oxidator for the derivation of the oxygen-rich fraction and at least one nitrogen line for the derivation of the nitrogen-rich fraction are provided, wherein the

Oxidator leads into a region of the vessel, which is arranged radially further away from the axis of rotation than a region of the vessel into which opens the nitrogen line.

That is, the air _Z erlegungseinheit (nitrogen) operates by means of fractional crystallization due to a

Pressure gradients (in the liquefied air), which principle is already known per se, cf. e.g. WO 2014/206792 Al.

 The liquefied air is at a certain level

Temperature before. The nitrogen crystallizes due to the pressure gradient at a certain first distance from the

Rotary axis, the crystals due to their compared to the liquefied air lower density in the direction of

Rotate the axis of rotation. At a second distance from the axis of rotation, which is smaller than the first distance, takes place due to the prevailing lower pressure there again

Liquefaction of nitrogen. This has the consequence that the liquefied air in a first region at the first distance from the axis of rotation has an increased oxygen content and in a second region at the second distance from the

Rotary axis an increased nitrogen content. By simply diverting the liquefied air (in the axial direction, parallel to the axis of rotation) from the respective area can be skimmed off according to the oxygen-rich or the nitrogen-rich proportion.

The operating state of the rotor rotation can be used in the present case to generate the pressure gradient or for driving the air _Z erlegungseinheit, which allows a seamless implementation of the air separation unit.

In addition, the air separation unit may include a per se known air liquefaction device, which in turn is connected upstream of an axial compressor or air inlet.

The counter-current principle can Erlegung _Z In this type of air are used to minimize the necessary refrigeration capacity and to achieve a very high efficiency. Ie Erlegung after air _{Z is} the separated components are already heated again, but due to the high pressure of the oxidant expands (as well as the nitrogen or the nitrogen-rich fraction) is not essential. However, it is not in the liquid, but in the gaseous phase, but the density is almost as high because of the pressure as in a

Liquid.

The nitrogen-rich fraction, which according to the above can be in liquid or gaseous form, can advantageously be used as a film jacket between the

Combustion gases and the inner wall of the main combustion chamber are mixed back to better protect the material of the main combustion chamber or the inner wall from damage, in particular by corrosion. In order to transport the nitrogen-rich portion with appropriate pressure to the designated locations of the main combustion chamber, again in the

Operating condition present centrifugal force are utilized, i. It can be used on additional facilities

Carriage of the nitrogen-rich fraction can be dispensed under high pressure. Therefore, it is at a special preferred embodiment of the device according to the invention provided that at least one nitrogen line is provided for discharging at least part of the nitrogen-rich portion from the air _Z unit, which is rigidly connected to the rotor and preferably in the rotor

is formed, wherein the at least one

Nitrogen at least partially extends radially up to the rocket engines to press in the operating state, the nitrogen-rich fraction by means of the centrifugal force present in the rocket engines by the rotation of the rotor, and that the at least one nitrogen line opens into nitrogen ring lines, each ring around one of the rocket engines in the area one

 Expansion region of a main combustion chamber of the expansion nozzle, wherein in the main combustion chamber, in particular in the expansion region, a plurality of openings are provided for the nitrogen-rich fraction and the respective nitrogen ring line opens into the openings. Accordingly, the

nitrogen-rich portion in the main combustion chamber, in particular in the expansion region of the main combustion chamber, introduced to form said film jacket, so that the combustion gases hardly or not come into contact with the inner wall of the main combustion chamber.

In this way, in principle, the entire

nitrogen-rich fraction to or into the

 Rocket engines (n) are derived. Possibly. However, it may be beneficial, the mass of the exhaust gas in relation to

to reduce introduced amount of fuel, e.g. in order to prevent a combination of the device according to the invention with a downstream steam turbine ("combined process"), that this "steam turbine generator" the exhaust gas draws too much energy. In this case, only part of the

nitrogen-rich portion of the rocket engines are fed, the remaining nitrogen-rich content can be outside be deducted or blown off. It may be noted that the steam turbine generator always withdraws energy from the exhaust gas, but the amount of heat proportional to the

oxidized fuel is, while the resulting from the combustion temperature increase is also reduced by the heat capacity of the back-mixed nitrogen-rich fraction. Thus in a combination process with already existing

Steam generator whose efficiency does not decrease, the temperature level should be maintained as possible over the state without rocket engines. Only part of the

to mix back nitrogen-rich portion, therefore, reduces the mass flow and the temperature level remains high despite the extracted by the steam turbine generator energy.

According to the above, a generator with the device according to the invention can be operatively connected to the

To allow drive of the generator by means of the device. In particular, the generator or a rotor of the generator can be non-rotatably connected to the rotor of the device.

In addition, as already mentioned, a frequency converter may be provided which is co-optimized with the generator.

According to the invention, a system for generating electrical energy is provided, the system comprising a device according to the invention and the generator.

The inventive device or the system according to the invention can be used to further increase efficiency with a

downstream steam turbine can be combined to form a combination process - analogous to the known gas and steam process. The rocket engines or rotating burners can be used for this purpose, e.g. in the combustion chamber of an existing one

Steam generator are introduced. Accordingly, it is in a preferred embodiment of the invention

Systems provided that a steam turbine is provided by means of the waste heat of exhaust gases of the rocket engines

is drivable. BRIEF DESCRIPTION OF THE FIGURES

The invention will now be explained in more detail with reference to an embodiment. The drawings are exemplary and are intended to illustrate the inventive idea, but in no way restrict it or even reproduce it.

Showing:

Fig. 1 is a schematic representation of a rotor of a

 Device according to the invention in plan view

Fig. 2 is a schematic representation of a sectional view through a rocket engine of the device according to the invention, wherein a longitudinal axis of

 Rocket engine is in the cutting plane

Fig. 3 is a schematic representation of an inventive

 System with a device according to the invention, to which a generator is coupled, in one

 Sectional view, wherein a rotation axis lies in the cutting plane

WAYS FOR CARRYING OUT THE INVENTION

In Fig. 1, a rotor 10 of a device according to the invention for driving a generator 3 for generating electrical energy in plan view is shown schematically. The rotor 10 is about a rotation axis 5, which in Fig. 1 normal to the

Drawing plane is, rotatably mounted.

At a radial distance D are on the rotor 10 more

Rocket engines 14 circumferentially arranged. In Fig. 1 is a circle 25 with radius D for clarity of illustration

drawn in dash-dotted lines. Im shown Embodiment eight rocket engines 14 are arranged regularly and at equal angular intervals to each other along this circle 25.

For a better overview is in Fig. 1 also a the

Rocket engines 14 and surrounding the rotor 10 surrounding 26 dashed lines. The circle 25 and the circumference 26 are centered about the axis of rotation 5, wherein the radius 26 clearly has a larger radius than the circle 25.

The rocket engines 14 are rigid with the rotor 10

connected. In this case, each rocket engine 14 is arranged so that its longitudinal axis 22 substantially tangentially touches the circle 25. The rocket engines 14 have open on one side combustion chambers, each having a corresponding opening 27 of the combustion chamber along the longitudinal axes 22 and in the view of FIG. 1 counterclockwise.

A measured along the longitudinal axis 22 length L of

Rocket engines is typically 0.15 m.

The combustion chambers of the rocket engines 14 are in the illustrated embodiment as expansion nozzles 9, which are sometimes referred to as Laval nozzles, formed and correspondingly have a main combustion chamber 9.11 and an adjoining expansion area 9.12 on.

Furthermore, in the illustrated embodiment includes a pre-combustion chamber 9.10 to the main combustion chamber 9.11, see. Fig. 2. A clear cross section of the expansion nozzles 9 has a constriction 15 between the pre-combustion chamber 9.10 and the

Main combustion chamber 9.11 on. Along the longitudinal axis 22 and seen from the constriction 15 of the expansion region 9.12 ends with the opening 27th

In an operating state of the device encounter the

Rocket engines 14 from the openings 27 support mass and thus drive the rotor 10 rotationally by the

Rocket engines 14 rotate along the circle 25 about the axis of rotation 5. By the rotor 10, in particular on the

Rotary axis 5, the generator 3 is coupled, the

Device so the generator 3, more precisely a rotor of the generator 3, rotationally driving, see. Fig. 3. The

Conversion of the electrical energy generated by the generator 3 to the mains frequency of a low-voltage power network can be carried out in a manner known per se, e.g. done electronically, especially using frequency converters.

Typically, the rotor 10 may be by means of the rocket engines 14 in the operating condition with operating speeds, corresponding to an integral multiple of the line frequency and in the range of 9,000 min ^-1 to 36,000 min ^-1, for example at 18,000 min ^-1, are driven.

By said operating speed can be achieved that the peripheral speed - ie the tangential velocity of the respective expansion nozzle 9 and the respective

Rocket engine 14 at the above-mentioned radial distance D - corresponds approximately to the exhaust gas velocity and the velocity of the ejected support mass, so that the energy release is maximized in a single-stage expansion process, such. 1500 m / s. One possible parameter combination is e.g.

a speed of 18000 min ^-1 and a radial distance D of 0.8 m. In this case, a centrifugal acceleration of about 290000 g occurs.

In the exemplary embodiment shown, the rotor 10 is designed to be both light and high-strength, the structure of the rotor 10, in particular in regions of support structures 9.7, comprising carbon fibers in a heat and pressure-resistant matrix of silicon carbide. The carbon fibers run in the support structures 9.7 parallel to the longitudinal extent of the respective support structure 9.7 and thus coarse - in the illustrated Embodiment up to about 22 ° - parallel to the centrifugal forces occurring.

As can be clearly seen in particular from FIG. 3, an outer radial section 21 of the rotor 10 in which the

Rocket engines 14 are arranged arranged in an exhaust space 4. The exhaust gas space 4 is through a housing 7 (off

For reasons of completeness also shown in Fig. 1) gas-tightly separated from a working space 6, wherein a

Non-contact seal 8 is provided, which allows the gas-tight passage of the rotor 10 through the housing 7. In the working space 6, an inner radial portion 23 of the rotor 10 is arranged, wherein the working space 6 can be evacuated to allow the operating state of the device, the arrangement of the inner radial portion 23 of the rotor 10 in vacuum. As can be seen in particular from Fig. 3, is located in

Operating state thus an essential part of the existing mechanics in a vacuum, so that surfaces exposed to the rapidly moving exhaust gases of the rocket engines 14 are minimized, which in turn beneficial to the

Stability of the device according to the invention affects.

In order to supply fuel to the rocket engines 14, the centrifugal force occurring in the operating state is utilized.

As can be clearly seen in FIG. 3, is shown in FIG

Embodiment in the region of the axis of rotation 5 a

fixed supply line 13 provided for the fuel. The supply line 13 opens into a plurality of fuel lines 13 ', which are circular in the region of the axis of rotation 5 or merge in a central circular recess 28. Opposite the working space 6, the fuel line 13 'or the recess 28 in said mouth region or in the region of the axis of rotation 5 by means of a gas or vacuum-tight

Seal 24 sealed. The fuel lines 13 'are rigidly connected to the rotor 10 and preferably formed in the rotor 10. The

Fuel lines 13 'extend radially to the rocket engines 14, so that in the operating state of

Fuel is pressed by means of the present by the rotation of the rotor 10 centrifugal force in the rocket engines 14.

Specifically, in the illustrated embodiment, the

Fuel in each case by a fuel supply end portion 9.1 of the fuel lines 13 'pressed into the Vorbrennkammern 9.10.

The fuel is using an oxidizer, which in the illustrated embodiment to

oxygen-enriched air is burnt. In the following, "oxygen" means the oxidizer, unless explicitly stated otherwise, the oxidizer may be in the liquefied or gaseous state.

Also, the oxidizer is supplied to the rocket engines 14 with the aid of centrifugal force. In the illustrated

Exemplary embodiments are oxidizer lines 12

provided, which are rigidly connected to the rotor 10 and are preferably formed in the rotor 10. In this case, the Oxidatorleitungen 12 extend radially to the

Rocket engines 14 in order to operate the oxidizer by means of the present by the rotation of the rotor 10

Centrifugal force in the rocket engines 14 to press.

Specifically, in the illustrated embodiment, the

Oxidator each by an oxidizer 9.4 in the

Pre-combustion chambers 9.10 pressed. Furthermore, the result

Oxidatorleitungen 12 in Oxidatorringleitungen 9.2, each annular to one of the rocket engines 14 in the region of a transition 16 of the main combustion chamber 9.11 to

Expansion area 9.12 of the expansion nozzle 9 run. The Oxidator ring lines 9.2 each open into channels 9.9 in a wall of the respective expansion nozzle 9, which channels 9.9 extend from the region of the transition 16 into the region of the constriction 15 of the respective expansion nozzle 9. This results in a regenerative cooling of the main combustion chamber 9.11 of

Expansion nozzle 9 and at the same time a preheating of the

Oxidizer.

In the Vorbrennkammern 9.10 are in each case in the range of

Constriction 15 provided a plurality of openings 17 for the oxidizer, in which openings 17 Oxidatorzufuhrendabschnitte 18 open, wherein the channels in the Oxidatorzufuhrendabschnitte 18

pass. The oxidizer supply end portions 18 and the

Openings 17 are designed such that, in the operating state, the oxidizer is pressurized to at least 1500 bar,

preferably from 2000 bar to 6000 bar, more preferably from 2500 bar to 5000 bar, is introduced in the direction of the constriction 15 in the pre-combustion chamber 9.10 to the fuel in the region of the constriction 15 in particles or droplets

Diameters of less than 10 ym to crush. In particular, the Oxidatorzufuhrendabchnitte 18 together with openings 17 thereto each star-shaped and the constriction 15 may be arranged facing.

As is apparent from Fig. 3, which shows a system according to the invention of the device according to the invention and the generator 3, the device according to the invention comprises in

illustrated embodiment also a

Air separation unit 2 (shown for clarity in Fig. 3 along the axis of rotation 5 shown interrupted, wherein the interruption is indicated by the two broken lines), which is coupled to the rotor 10. The

Air separation unit 2, in turn, includes a per se known air liquefaction device (not shown, can in particular in the region not shown

Be arranged interruption) for the liquefaction of air, wherein the air liquefaction device is preceded by an air inlet with an axial compressor 1 in order to suck in the air to be liquefied.

The air _Z erlegungseinheit 2 is provided in order to divide the liquefied air into a nitrogen-rich fraction and an oxygen-rich fraction and to use the oxygen-rich fraction as the oxidizer, wherein the oxidizer, as already mentioned, may not necessarily be in liquid form, but can also be used in gaseous form. The air erlegungseinheit _Z 2 comprises a rotatable around the rotation axis 5, fixed to the rotor 10 connected container 19 for the liquefied air. In the vessel 19 is formed in the operating condition by rotation, a pressure gradient in the liquefied air to produce by means of fractional crystallization, the oxygen-rich fraction so that the

oxygen-rich fraction in the vessel 19 is arranged radially further away from the axis of rotation 5 than the nitrogen-rich fraction.

This decomposition principle is already known per se, cf. e.g. WO 2014/206792 Al. The liquefied air is present at a certain temperature. Due to the pressure gradient, the nitrogen crystallizes at a certain first distance from the axis of rotation 5, the crystals migrating in the direction of the axis of rotation 5 due to their lower density compared to the liquefied air. At a second distance from the axis of rotation 5, which is smaller than the first distance, takes place due to the prevailing there lower pressure again liquefaction of the nitrogen. This has the consequence that the liquefied air in a first region at the first distance from the rotation axis 5 has an increased oxygen content and in a second region at the second distance from the rotation axis 5 has an increased nitrogen content. By

simple discharge of liquefied air (in axial

Direction, parallel to the axis of rotation 5) from the respective area can according to the oxygen-rich or the nitrogen-rich fraction are skimmed off. As a result, due to heating, the oxygen-rich fraction and / or the nitrogen-rich fraction can change from the liquid state to the gaseous state. That is also the

nitrogen-rich fraction may be in gaseous form

continue to be used.

Accordingly, in the illustrated embodiment, the Oxidatorleitungen 12 for discharging the oxygen-rich

Share and nitrogen lines 11 for the derivation of

nitrogen-rich fraction provided, the

Oxidator 12 lead into a region of the vessel 19, which is located radially further away from the axis of rotation 5 as a region of the vessel 19, in which the nitrogen lines 11 open.

The nitrogen-rich fraction is shown in the

Embodiment - at least partially - also fed to the rocket engines 14, by one

form protective film coat in the respective main combustion chamber 9.11. This again takes place by utilizing the centrifugal force. For this purpose, the nitrogen pipes 11 are not only rigidly connected to the rotor 10 and preferably formed in the rotor 10, but extend radially to the

Rocket engines 14 to operate in the operating state

nitrogen-rich portion by means of the present by the rotation of the rotor 10 centrifugal force in the

Rocket engines 14 to press. The nitrogen lines 11 open into nitrogen ring lines 9.3, which extend in each case annularly around one of the rocket engines 14 in the expansion region 9.12 of the main combustion chamber 9.11 of the expansion nozzle 9. In the respective main combustion chamber 9.11, in particular in

respective expansion region 9.12, a plurality of openings 20 are provided for the nitrogen-rich portion, wherein the

respective nitrogen ring line 9.3 opens into the openings 20, cf. Fig. 2. More specifically, the supply of the nitrogen-rich portion to the openings 20 in that region, which lies between the constriction 15 and the transition 16, via internal

Nitrogen ring lines 9.8, with the

 Nitrogen ring lines 9.3 (fluid) are connected. That In this area, the inner nitrogen ring pipes 9.8 open into the openings 20.

Accordingly, the nitrogen-rich fraction in the

Main combustion chambers 9.11 and the expansion areas 9.12

introduced to form said film jacket, so that the combustion gases with the inner wall of the main combustion chambers 9.11 and the expansion areas 9.12 little or not at

Come in contact.

To further minimize corrosion and abrasion of the

Combustion chambers 9.10, 9.11, 9.12 are these in the shown

Embodiment by a metal sheath 9.5 made of a temperature-resistant superalloy, such. IN909, with an inner ceramic coating 9.6, e.g. made of aluminum oxide, formed. The ceramic coating 9.6 is biased by the metal shell 9.5 to pressure.

To regulate the amount of fuel and / or the

Oxidizer and / or nitrogen-rich portion, a throttle 29 may be provided in each case. The throttles 29 are in

illustrated embodiment in the rotor 10, more precisely arranged in the inner radial portion 23, cf. Fig. 3. LIST OF REFERENCE NUMBERS

1 Axial compressor

2 Air _Z erlegungseinheit

 3 generator

4 exhaust gas space

 5 axis of rotation

 6 workspace

 7 housing

 8 Non-contact seal

9 expansion nozzle

 9.1 fuel supply end section

 9.2 oxidizer ring line

 9.3 nitrogen ring line

 9.4 Oxidator feed pre-combustion chamber

9.5 Metal jacket

 9.6 Ceramic coating

 9.7 Support structure

 9.8 Inner loop nitrogen

 9.9 Regenerative cooling channels 9.10 Pre-combustion chamber

 9.11 main combustion chamber

9.12 Expansion area 10 rotor

11 Nitrogen line or line for (liquefied or gaseous) air with nitrogen-rich content

12 oxidizer line or line for (liquefied or gaseous) air with oxygen-rich content

13 Supply line for fuel 13 'fuel line

14 rocket engine

15 constriction

16 transition

17 opening for oxidizer

18 Oxidator feed tail

Erlegungseinheit vessel 19 the air _Z

20 opening for nitrogen-rich fraction

21 Outer radial section of the rotor

22 longitudinal axis of a rocket engine

23 Inner radial section of the rotor

24 Sealing of the fuel line

25 circle with radius D

26 perimeter

27 opening

28 recess

29 throttle D Radial distance

L Length of the rocket engine

Claims

1. Device for driving a generator (3) for generating electrical energy, the device comprising a rotor (10) rotatably mounted about a rotation axis (5), wherein on the rotor (10) at a radial distance (D) to the rotation axis (5) several rocket engines (14) open on one side  Combustion chambers circumferentially arranged and rigidly connected to the rotor (10) are connected to in an operating state of  Circling around the rotation axis (5) and thus rotationally driving the rotor (10) about the rotation axis (5), wherein the combustion chambers are preferably designed as expansion nozzles (9), characterized in that the structure of the rotor (10) carbon fibers in a heat and a  pressure-resistant matrix, preferably of silicon carbide, wherein more than 50%, preferably more than 66%, of the carbon fibers are arranged so that the respective  Carbon fiber runs transversely to a tangent, the  Tangent passes through a point on the respective carbon fiber and tangential to an auxiliary circle at this point, which auxiliary circle is centered about the axis of rotation (5) and arranged in a plane normal to the axis of rotation (5) and passes through the point. 2. Apparatus according to claim 1, characterized in that the course of the respective carbon fiber with the tangent at an angle of 55 ° to 90 °, preferably from 65 ° to 90 °, includes. 3. Device according to one of claims 1 to 2, characterized  characterized in that an outer radial portion (21) of the rotor (10) in which the rocket engines (14) are arranged in an exhaust space (4) is arranged that from the outer radial portion (21) of the rotor (10) to the axis of rotation (5) seen from a housing (7) the exhaust gas space (4) gas-tightly limited, and that between the housing (7) and the rotation axis (5) a working space (6) is arranged, in which an inner radial portion (23) of the rotor (10) is arranged, and wherein the working space (6) is evacuated, in the operating state of the device, the arrangement of the inner Radial section (23) of the rotor (10) to allow in vacuum. 4. Device according to one of claims 1 to 3, characterized characterized in that in the operating state of the rotor (10) is drivable at an operating speed which is in a range of 9000 min ^-1 to 36000 min ^-1 , preferably from 16000 min ^-1 to 24000 min ^-1 , and preferably an integer multiple of one Frequency of a low-voltage power network is. 5. Device according to one of claims 1 to 4, characterized  characterized in that in the region of the axis of rotation (5) a fixed supply line (13) is provided for fuel, which opens into at least one fuel line (13 '), wherein the at least one fuel line (13') with the rotor (10) is rigidly connected and preferably in the rotor (10), wherein the at least one  Fuel line (13 ') radially to the  Rocket engines (14) extends to press in the operating state, the fuel by means of the present by the rotation of the rotor (10) centrifugal force in the rocket engines (14). 6. Apparatus according to claim 5, characterized in that the combustion chambers each as an expansion nozzle (9) with a pre-combustion chamber (9.10) and an adjoining  Main combustion chamber (9.11) are executed, wherein a light cross-section of the expansion nozzle (9) between the  Pre-combustion chamber (9.10) and the main combustion chamber (9.11) has a constriction (15), wherein the at least one Fuel line (13 ') in a Passes fuel supply end portion (9.1), which opens into the pre-combustion chamber (9.10). 7. Device according to one of claims 5 to 6, characterized  characterized in that at least one Oxidatorleitung (12) is provided, which is rigidly connected to the rotor (10) and is preferably formed in the rotor (10), wherein the at least one Oxidatorleitung (12) at least  sections radially up to the rocket engines (14) extends to in the operating state an oxidizer by means of the rotation of the rotor (10) present  Centrifugal force in the rocket engines (14) to press. 8. Apparatus according to claim 7 and claim 6, characterized  in that in each case in the pre-combustion chamber (9.10) in the region of the constriction (15) a plurality of openings (17) are provided for the oxidizer, in which openings (17) Oxidatorzufuhrendabschnitte (18) open, said  Oxidatorzufuhrendabschnitte (18) and the openings (17) are designed such that in the operating state, the oxidizer at a pressure of at least 1500 bar, preferably from 2000 bar to 6000 bar, more preferably from 2500 bar to 5000 bar, in the direction of the constriction (15 ) in the pre-combustion chamber (9.10) can be introduced to comminute the fuel in the region of the constriction (15). 9. Device according to one of claims 7 to 8 and claim 6, characterized in that the at least one  Oxidator (12) in Oxidatorringleitungen (9.2) opens, each annular to one of the rocket engines (14) in the region of a transition (16) of the main combustion chamber (9.11) extend to an expansion region (9.12) of the expansion nozzle (9), and that the Oxidatorringleitungen (9.2) each in channels (9.9) in a wall of the respective Expansion nozzle open, which channels (9.9) from the area of Transition (16) in the region of the constriction (15) of the respective expansion nozzle (9) extend. 10. Device according to one of claims 1 to 9, characterized  characterized in that the combustion chambers from a  temperature-resistant alloy with oxidation-resistant  Material (9.5) are formed and a  Ceramic coating (9.6) have. 11. Device according to one of claims 1 to 10, characterized in that an air erlegungseinheit _Z (2) is provided in a liquefied air  decompose nitrogen-rich fraction and an oxygen-rich fraction and to use the oxygen-rich fraction as oxidizer. 12. The device according to claim 11, characterized in that the air _Z erlegungseinheit (2) comprises a rotatable about the axis of rotation (5), with the rotor (10) rigidly connected vessel (19) for the liquefied air, in which vessel (19 ) In the operating condition by rotation, a pressure gradient in the liquefied air can be formed in order to  fractionated crystallization to produce the oxygen-rich portion so that the oxygen-rich portion in the vessel (19) radially further away from the axis of rotation (5) is arranged as the nitrogen-rich fraction, and that at least one Oxidatorleitung (12) for discharging the oxygen-rich portion and at least one Nitrogen line (11) are provided for discharging the nitrogen-rich portion, wherein the Oxidatorleitung (12) opens into a region of the vessel which is located radially further away from the axis of rotation (5) than a portion of the vessel (19) into which the nitrogen line (11) opens. 13. Device according to one of claims 11 to 12, characterized characterized in that for the discharge of at least part of the nitrogen-rich fraction from the air _Z unit (2) at least one nitrogen pipe (11) is provided, which is rigidly connected to the rotor (10) and is preferably formed in the rotor (10), wherein the at least one nitrogen pipe (11) at least partially radially up to the rocket engines (14 ) in order to be in the operating state, the nitrogen-rich fraction by means of the rotation of the rotor (10) present  Centrifugal force in the rocket engines (14) to press, and that the at least one nitrogen line (11) in nitrogen ring lines (9.3) opens, respectively  annular around one of the rocket engines (14) in the region of an expansion region (9.12) of a main combustion chamber (9.11) of the expansion nozzle (9), wherein in the main combustion chamber (9.11), in particular in the expansion region (9.12), a plurality of openings (20) are provided for the nitrogen-rich portion and the respective  Nitrogen ring line (9.3) opens into the openings (20). 14. System for generating electrical energy, comprising a device according to one of claims 1 to 13 and the generator (3). 15. System according to claim 14, characterized in that a steam turbine is provided which can be driven by means of the waste heat of exhaust gases of the rocket engines (14).