DE10214535A1 - Power unit for light aircraft has four-bladed shrouded propeller or jet, and combustion engine of spiral relief motor used in combination with compressor - Google Patents

Abstract

The power unit has a four-bladed shrouded propeller, or possibly a jet, running at high revs., and achieving as much thrust as possible from a unit of as small a diameter as possible A spiral or other compressor is also used, partly as a relief motor. This too can run at high revs. The combustion chamber has fuel injection jets.

Description

The invention relates to a method for operating various types of personnel Flight cars as well as the constructive versions of this flight apparatus and its drives.

In the patent literature regarding the personal flight car, with regard to small ones Aircraft with a vertical take-off landing, the author has so far found no publication except for U.S. Patent 3,785,592 and WO 96/07586, relating to round aircraft Wings, but only as an idea, without further interpretations with regard to energetics. Patent WO 95/07215 describes a "combination aircraft" with lifting rotor, wing, two March propellers and two engines, even without further interpretations with regard to the Energetics. This flying machine is not a mini flying machine.

In the public literature one can find claims that some copies of such Technology already exist. Der Spiegel 52/1999 reports of a "Skycar" prototype of the Designer Moller, a kind of Bat-Mobil for the people with four seats and eight Wankel engines, which the author also subjected this mirror report to real flight tests wanted to. In Der Spiegel 23/1999 and 15/2000 there are small notes about "SoloTrek" by the visionary Moshier and about a helicopter for everyone, by the Japanese company Engineering System is built. But to this day you can't see a Bat-Mobil for the people in everyday life or observe.

The main problem with flight cars is focused on the propulsion system.

Regarding small flying machines, where problems of weight and dimensions and even the Configuration of the drive system play the most important role, play work processes and the constructive scheme of this plant is of crucial importance.

The combination of a trivial internal combustion engine with propeller (screws) as with Airplanes and helicopters are less suitable for the mini-aircraft; because that Power mass for internal combustion engines (1.5-4 kg / KW), due to space-consuming, heavy crankshaft mechanism with surrounding housing and operating instructions, also by mechanical reduction gear or transmission to the propeller (screws) too large. The working method of the internal combustion engine limits the speed of the Engine and can therefore no steady and ongoing supply of energy to the Ensure propeller.

Jet gearboxes are also not suitable for a mini flying car. Your fuel consumption is too high, and so far they are not very suitable for operating a mini flying machine.

A jacketed propeller as the operator is at a vertical start and relatively low speeds many times more effective than a jet gearbox, all the more so when you look at the multi-blade propeller new generation speaks. But engine problems nonetheless exist.

The best way to solve problems of the engine for propeller propulsion is from the invention of the engines with a uniform working method and High speeds. This allows a significant weight gain to be achieved, regardless that a reducer is indispensable.

The second important requirement is that the engine is at best in the middle of the propeller is housed and must be spindle-shaped, especially since the zone around the axis of the propeller is not very effective.

The long-known Wankel engine or its modification, e.g. B. WO 95/16116, WO 96/11334, WO 96/12878, or WO 98/49435 as well as different types of rotary and rotary piston Motors (WO 96/23135; EP 0747586 A1; WO 96/41934, WO / 41935; WO 97/10419; EP 0785348 A1; WO 97/34078; DE 432 49 558 A1; DE 43 24 997 A1; WO 95/05534; DE 43 35 878 A1; DE 44 36 822 A1; WO 95/08055; WO 96/17161; WO 96/21096; WO 99/35382; WO 99/46494 and more) are more or less closer to the engine, which are even and works at high speeds. So far, these motors have not been widely used for the Drive of the mini aircraft found. The reason for this is the presence of free mass forces, which limits the speed of the machine, which results in an increased size and weight. In addition, some tried and tested machines suffer from increased wear and tear Compression parts or are too complicated to manufacture.

There is still a class of internal combustion engine combination of screw Compressor and screw-type expansion engine that burns fuel before the Screw expansion motor provides and that in DT 25 00 816 A1; G 91 11 849.2; G 94 01 804.9; WO 00/77363 A1; WO 00/77364 A1 more or less suitable for solving the Problems drive system for mini-flight cars is shown. So it turns out that the The main idea and the design scheme of the suitable engine are already patented. These patents have to be viewed as prototypes.

The drive system claimed as an invention (including multi-blade propeller and jacket), which could ensure the required ongoing working process at high speeds, is shown in FIGS. 1, 2 and 3.

The propeller ( 2 ) is only shown to a limited extent, because its real shape can only be determined after extra calculations. It is a propeller of this new generation, which is equipped with 8-12 swept blades. It's about a "pro fan", because as a multi-blade propeller it already represents a transition stage to a FAN, ie to a blower.

Even the engine consists of three main parts: screw compressor ( 8 ), combustion chamber ( 9 ) and relaxation screw motor ( 10 ).

The state of the art shows that single-stage screw compressors with oil injection for compression and cooling according to the type of screw or Lysholm compressors with circular arcs, epicycloids and envelopes as contour parts of the rotor with speed up to 25000 l / min in the range of the flow rate of V = 0.03-12 m ³ / s and final pressure up to 10 bar can work. A single-stage screw compressor with oil injection cooling F 37/10 (Tamrock-Tampere-Finland) provides a flow rate of 300 m ³ / h (80 L / s), final pressure 1 Mpa (10 bar) with an engine output of 37 kW.

These characteristics also apply accordingly to single-stage, flow-rate-controlled refrigerant screw compressors with oil injection cooling S 3-900 (VEB Kühlautomat Berlin):
Flow rate 770 m ³ / h; Final pressure 2.25 MPa (22.5 bar); Speed 2940 l / min. (Taschenbuch Maschinenbau, VEB Verlag Technik, Berlin, 1989, volume 5, pp. 286, 287; Dubbel, paperback for mechanical engineering, 17th edition, Springer-Verlag Berlin, Heidelberg, 1990, see P 44).

The wear is low, there are no free inertial forces. They are disadvantageous small efficiencies. Therefore, the production has to be very precise. So they owe theirs Widespread use of the improved hobbing process recently. (Verter, G., ed .: Handbuch Compressor, 1st edition, Essen; Vulkan Verlag 1990).

Thanks to good characteristics of performance and dimensions, as well as uninterrupted Working method is one use of this type of screw compressor in reverse Scheme, namely as a relaxation motor, very useful.

For this you still need a combustion chamber with injectors for the supply of Energy from fuel.

The work processes in expanding channels of the rotor of this screw motor at their Rotations correspond to the processes of piston displacement in combustion engines, with the difference, however, that these processes are ongoing and uninterrupted. All Preparation processes, indispensable for conventional internal combustion engines, are no longer necessary. This eliminates gas valve devices and crankshaft mechanisms with their comprehensive housings, with their weights and free mass forces. The Working revolutions of the engine can be increased several times, which with the same performance of the Motors gives the decisive gain in weight.

Simple calculations could support these conclusions.

For example, for an aircraft with a total weight of m = 1000 kg and two engines Diameters of the jacket propeller D = 120 cm can be calculated:

The highest value of the speed of the propeller n can be calculated with the proviso that the speed of the propeller tip is in the subsonic range, i.e. at Mo, max = 0.8 limit values.

Relative starting thrust value of each of the two engines for vertical takeoff F:

The thrust / power ratio can be estimated assuming a standard grade η _{p, g o} = 0.75 for an 8-12 blade propeller. (Urlaub, Alfred: Flugtriebwerke Springer-Verlag 1991, pp. 122-130)

Assuming the engine power for air compressors P ₁ = 0.25 P and the efficiency of the engine η = 0.75 calculated engine power Pm = 240 KW

Starting from the value of the torque of the motor assuming the mean pressure in the channels of the rotor Pmittl. = 15 bar and the length of the rotor L = 1.5D, one could estimate the diameter of the rotor D:

M _M = Pmittl. L 0.375 DD = 10.5 cm

Approximate dimensions of the engine:
Diameter of the machine DM = 30 cm; Length LM = 65cm
Approximate evaluation of the weight of the engine assuming the specific weight of the construction q = 2.5-3 kg / L:

The value of the power mass = 0.5 kg / KW is therefore considerably lower than the limit value for conventional internal combustion engines with power mass = 1.5 kg / KW.

So a mini flying machine with two engines and the total mass needs m = 1000 kg 2 times 240 = 480 KW of power, whereby even 2 engines together 240 kg to weigh.

This result is with very rough calculations and generous assumptions calculated. After precise calculations and experiments you can get significantly better results achieve. The main problem is ensuring the appropriate heat regime and achieving it good values of efficiencies, which is related to the price of manufacturing the runners stands.

Fig. 1 shows an engine consisting of an engine ( 1 ), propeller ( 2 ), jacket ( 3 ), spar ( 4 ) with connection transmission ( 5 ) and built-in parts ( 6 ) together with electromagnetic multi-plate clutch with auxiliary engine (not shown in detail).

In Fig. 2, the engine including the reduction gear ( 7 ) and several cuts is shown.

The screw compressor ( 8 ) together with the pair of teeth ( 12 ) is asymmetrically assigned to the screw expansion motor to create space for a pre-compressor device (not shown in detail) with filter ( 11 ), as well as for a pair of teeth ( 13 ) for the kinematic Connection to an auxiliary engine including two roller lock clutches on the shaft of the engine ( 14 ). The rest of the room can be used for operating units such as constant feed pumps for fuel, oil, cooling liquid, as well as for starters, dynamos (all not shown in detail) and other units.

The combustion chamber ( 9 ) as a separate unit is designed so that a well-ordered combustion process could be set up. This relieves the heat regime of the machine and fulfills a complete combustion process of the fuel, which in turn leads to a better value for the efficiency of the machine and a minimized environmental impact.

The combustion chamber is designed as a direct current combustion chamber with a burner ( 15 ), swirl body ( 16 ), rib elements ( 17 ) and spark plugs ( 18 ) and enables the use of any type of cheap fuel.

The screw expansion engine ( 10 ) is supplied with devices for injection for oil and oil-fuel mixture (not shown in more detail), which results in better compression between the rotor and walls in dry-running engines and enables an afterburning process in the expansion engine. The afterburning process creates a more even distribution of the pressure drops along the rotor, which enables an improvement in efficiency.

In addition, an increased injection of the oil-fuel mixture serves to force the engine regime, which could take over the drive of the propeller of the adjacent engine by means of teeth pair ( 13 ), transmission ( 5 ) and electromagnetic multi-plate clutch if his own engine fails. The roller lock clutch ( 14 ) makes it possible to exclude it when the engine fails.

A heat-resistant disc ( 19 ) enables calibration of the inlet opening in the expansion motor. Bearing devices ( 20 ) and pair of teeth ( 21 ) provide the required arrangement of the rotor pairs during their rotation at speeds of up to 25,000 l / min, which ideally should not be in contact. The heat regime in the bearing of the expansion motor and compressor, as well as in the heat-stressed parts of the machine, provides coolant which, conveyed by a constant feed pump, flows through corresponding channels and transfers its heat to the air flow in a cooler ( 22 ).

The exhaust gases from the expansion engine are still a high-energy medium and can therefore be expanded in a jet nozzle ( 23 ) and thereby increase the performance of the engine.

Since the screw expansion motor has two shafts rotating in the opposite direction, the engine can also be supplied with a second propeller rotating in the opposite direction to the first. Then there is the possibility of parrying the reactive moment of the first propeller and thus facilitating the sole use of the engine for the mini-aircraft. This creates a second modification of the engines, which is shown in FIG. 3. Here you need a second reduction gear ( 24 ) and another spar without transmission. The gear wheel ( 13 ) only operates operating units. The jacket ( 3 ) extends to the second propeller. Some oblique ribs in the wall of the jacket ( 25 ) are provided in order to allow leveling to finally eliminate the reactive moment.

In this case, the exhaust gases can be discharged and used in the space between the propellers also increasing the performance of the engines.

If you have two such engines, you can do different types of Construct flying machines.

First, it can be the one- or two-seater with only one two-propeller engine. It could have the shape of a saucer missile, as shown in FIG. 4. The engine must be arranged in a tunnel ( 26 ) in the middle of the fuselage and the cockpit ( 27 ) by means of pylons ( 28 ) above the tunnel.

The tunnel in the fuselage of the aircraft has a number of devices such as vise drives ( 29 ) for adjusting and displacing the engine hanger, the steering of the apparatus being able to advance and its inclination to make the curves possible.

A steerable surface ( 30 ) accommodated between pylons is provided as a rudder for rotation at the point after the aircraft has been lifted off the ground.

An engine develops a powerful stabilizing moment thanks to the gyroscopic effect with the engine running and the rotating propeller. This serves the safety of the flight, but on the other hand it creates problems of maneuverability. In any case, all maneuvers are fluent. With the control command via joystick, the vise drive ( 29 ) adjusts the casing of the engine in the tunnel so that the center of the weight deviates from the vector of the thrust, then the resulting control moment gradually inclines the vector of the thrust in the corresponding direction.

The best possible safe and economical variant of the personal flight car is shown in FIG. 5. The shape of the apparatus corresponds to the shape of an aircraft with thick wings, which enables the advantages of its corresponding aircraft properties to be used in horizontal flight.

Two engines arranged side by side in their own tunnel, each with one in the opposite direction mantle rotating propellers near the center of the weight of the whole Aircraft are housed in the thick wings.

The advantage of this scheme is that the two engines are placed close to each other a kinematic connection and thus the takeover of the energy supply of the propellers both engines in the event of one engine failing due to the adjacent engine alone enable. This at least ensures a safe landing.

The kinematic connection allows a separate control of the engines to tilt in Advance direction and regime to what all maneuvers on the spot and advancing enables (see previous description of the design of the engines).

The important advantage of this scheme is also that reactive moments of both Engines neutralize each other. This eliminates the need for special Stabilization and steering devices like helicopters with only one rotor.

In FIG. 6, a third low cost version of the flying machine is shown.

The shape of the fuselage corresponds to the shape of the saucer missile. Four engines with each a mantle propeller, housed in its own tunnel, are arranged in pairs in the wing. The cabin of the apparatus can be built hermetically to the water and thereby Swim skills get what the execution of the flying apparatus as an amphibian and thus the increase its area of application to the ambulance, to the emergency vehicle for police everywhere, Fire brigade and so on, or simply to the flight yacht.

Claims (28)

1. A method of operating a vertical take-off and horizontal flight apparatus in which the thrust is generated by a propeller operated by the internal combustion engine in the middle of the propeller, the vector of the thrust being changed by tilting the axis of the engine can, is characterized in that the propeller is a multi-blade jacketed propeller or even a blower and the internal combustion engine is represented by a screw-type expansion motor in combination with a screw-type compressor and a combustion chamber. 2. The method according to claim 1, characterized in that the speed of the Multi-blade jacketed propellers in the high speed range at the propeller tip 0.8M lies and therefore has relatively small dimensions, what a small Aircraft like the passenger flight car is of great importance. 3. The method according to claim 1, characterized in that the screw Relaxation motor is inherently a screw compressor, the reverse Scheme, i.e. works as a relaxation motor and therefore a flowing one Working method that could happen at very high speeds - limited only through the working conditions of the warehouse - and as such the decisive profit of the dimensions and weight of the power plant. 4. The method according to claim 1, characterized in that in the combustion chamber, the is installed as an intermediate stage, a well-ordered combustion process is set up could relieve the heat regime and become complete The fuel combustion process results in any type of cheap fuel could be used and the environmental impact could be minimized. 5. The method according to claim 1, characterized in that the screw Relaxation motor, since it has two screw rotors that are not in contact has, with an oil injection for the compression stage and an oil-fuel Mixture for injection into the relaxation stage could work, resulting in a high degree of compression on the one hand and an afterburning process in the Relaxation level, on the other hand, leads to increased efficiency achieve enables. 6. The method according to claim 1, characterized in that the screw Relaxation motor is supplied with two shafts rotating in the opposite direction Application of the two propellers rotating in the opposite direction enables and thereby one disturbing reactive moment is absent, which for the aircraft with only one Drive system is of great importance. 7. The method according to claim 1, characterized in that for the transfer of the Torque from the engine (at speeds up to 25000 l / min) to the propellers (at a speed of 4600 l / min with a diameter of 1.2 m, as an example) Reduction gear is provided. 8. The method according to claim 1, characterized in that exhaust gases which are still a Represent high energy medium, be consumed in a jet nozzle or in the Space between the propellers are fed, which in turn increases the Efficiency. This also applies to cooling heat generated by the cooling current Housing and through the cooling system into the space between the propellers. 9. The method according to claim 1, characterized in that the afterburning process in the relaxation stage as well as the increased regime in the combustion chamber enable a forced regime of work for the whole engine. Thereby this engine could also drive the propellers of the adjacent engines in the event of failure of their own engine, if both engines are in kinematic connection. This could at least be the safe one in an emergency Landing are guaranteed. 10. Design of the engines to implement the procedures according to Claims 1-9, which provides one or two propellers in a jacket, as well as one Internal combustion engine consisting of screw compressor, combustion chamber and Screw relaxation motor exists, as it is in DT 25 00 816 A1; G 91 11 849.2; partly in G 94 01 804.9; WO 00/77363 A1 and WO 00/77364 A1 is patented, characterized in that the jacketed propeller is a multi-blade jacketed propeller or Is blower; as well as that as a basic element for screw compressors as well a screw or Lysholm compressor with oil Injection is provided for better compression, the arc, epicycloid and Envelopes prove to be contour parts of the runners thanks to their good characteristics and technology has recently been widely used in manufacturing. (Taschenbuch Maschinenbau, Volume 5, VEB Verlag, Berlin, 1989 pp. 247, 284, 287; Dubbel, paperback for mechanical engineering, 17th edition, Springer-Verlag Berlin, Heidelberg, 1990, p. P44). 11. Engine according to claim 10, characterized in that a Lysholm compressor as a basic element for the screw relaxation motor in the reverse scheme works as a relaxation motor. 12. Engine according to claim 10, 11, characterized in that for the Screw relaxation engine provided an injection of oil-fuel mixture is, with better compression as well as even distribution of pressure drops along the runner and thus an improvement in efficiency can be achieved could. In an emergency, increased injection of the oil-fuel mixture is used for the forced Regime of the engine, as provided for in claim 9. 13. Engine according to claim 10, 11, characterized in that for the exploitation of the Rest of the pressure gradient, a nozzle drive is set up, as provided for in claim 8. 14. Engine according to claim 10, characterized in that the screw compressor is arranged asymmetrically with respect to the screw expansion motor and thereby Space is created for the combustion chamber, for the kinematic Coupling device with auxiliary engine and for other operating units. 15. Engine according to claim 10, 14, characterized in that the Screw compressor could still be supplied with an intake pre-compressor including filter. 16. Engine according to claim 10, characterized in that the combustion chamber as a separate facility with all the necessary elements for a proper Burning the fuel and getting the proper heat regime is built as provided in claim 4. 17. Engine according to claim 10, characterized in that the engine with a cooling system is supplied, the cooling channels, especially around the bearings that Constant feed pump and the air cooler includes. 18. Engine according to claim 10, characterized in that one or two Reduction gear for one or both propellers, as well as a spar with Components for connecting the engine to the jacket and units with Bearing for the installation of the engine in the aircraft. 19. Engine according to claim 10, characterized in that some ribs inside of the mantle are provided, which are a leveling and final elimination of the Enable reactive moments, as provided for in claim 6. 20. Engine according to claim 10, characterized in that a transmission for the Kinematic connection of the engines, including two Roller lock-up clutches on the shafts of the engines and an electromagnetic disk Clutch, between the two engines are provided. 21. Design of the engines according to claim 10, but without Jacked propeller, only one engine, characterized in that this force their economic viability other applications at the place of conventional Internal combustion engines or turbines could claim. 22. Construction of the personal flying apparatus for the vertical takeoff and horizontal flight with one, two or more engines, in which the Thrust generated by a propeller operated by the internal combustion engine in the middle of the Propeller, the vector of the thrust by tilting the axis of the engine can be changed, as is the case with conventional helicopters characterized in that this design the installation of the engine according to claim 1-20 has and corresponding facilities for control of engines and flight includes. 23. Construction of the personal aircraft with a two-propeller Engine according to claim 21, characterized in that the shape of the fuselage corresponds to the saucer missile, with a tunnel for this engine in the middle of the fuselage and the cockpit, which is attached to pylons above the tunnel. 24. Constructive design of the flying apparatus according to claims 21, 22, characterized characterized that the tunnel in the fuselage of the aircraft apparatus like the Vise drives for adjusting and moving the hanger of the engine has and thus a steering of the apparatus in advance and the inclination of the apparatus for the execution of the curves. 25. Constructional design of the flying apparatus according to claim 21, characterized in that that a steerable surface, attached between pylons, acts as a rudder for rotation the place is provided after the take-off of the aircraft. 26. Construction of the personal aircraft with two each in its own tunnel engines arranged side by side, each with a jacket propeller, which in Opposite direction to the adjacent propeller rotates, according to claim 21, thereby characterized in that the shape of the apparatus is the shape of an airplane with thick Wing corresponds, whose aircraft properties bring advantages in horizontal flight and thus increases profitability. 27. Constructional design of the flying apparatus according to claims 21, 25, thereby characterized that built-in steering devices of the engines and their separate control of the engines for kinematic connections Allow inclination in the direction of advance and regime and in the event of an emergency The power supply for the two propellers is taken over by one engine alone is made possible, as provided in claims 9, 20. 28. Construction of the personal flying apparatus with four each in its own tunnel Engines arranged in pairs next to each other, each with a jacket propeller Claim 21, characterized in that the shape of the hull of the saucer Missile, with its own tunnel for each engine in the wing, the The cabin is hermetically designed for water and has what swimming capabilities Execution of the flight apparatus as an amphibian and thus also the increase of his Application area as an ambulance, emergency vehicle for police everywhere Firefighters and so on, or simply as a flying yacht.