RU2554392C1 - Hydrogen gas turbine engine - Google Patents

Abstract

FIELD: motors and pumps.

SUBSTANCE: hydrogen gas-turbine engine contains an air inlet, a housing, a compressor with a compressor rotor with a shaft, a main combustion chamber installed downstream the compressor and an air path connected thereto and a supersonic jet nozzle. Between the compressor and the combustion chamber inside the air path connecting the compressor and the combustion chamber the hydrogen turbine is installed which has inlet and outlet headers. Downstream the combustion chamber the heat exchanger is installed the inlet of which is connected to the fuel-supply line, and the outlet - to the inlet header of the hydrogen turbine. The outlet header of the hydrogen turbine is connected through the pipeline to the main combustion chamber. Downstream the heat exchanger the second compressor is installed between which and the supersonic jet nozzle the afterburner is installed. The hydrogen turbine and the second compressor are connected with the compressor rotor shaft.

EFFECT: increase of compression ratio of the compressor, increase of engine thrust and improvement of its specific characteristics.

4 cl, 4 dwg

Description

The invention relates to engine building, specifically to aircraft engines for supersonic and hypersonic aircraft.

Known hydrogen gas turbine engine according to the patent of the Russian Federation for the invention No. 2029118, IPC F02C 3/04, publ. 05/20/1995, with an auxiliary circuit operating on hydrogen, an additional air path was introduced into the auxiliary circuit, connecting the outlet from the free compressor with the auxiliary chamber. Hydrogen in the engine circuit acts as a refrigerant. To cool the turbine of the main circuit, high-pressure air is used, which, after cooling the turbine, is supplied to the intermediate overheating combustion chamber, where liquefied air enters the gaseous state at the same time.

The disadvantage is the low specific characteristics of the engine due to the low degree of air compression in the compressor.

Known hydrogen gas turbine engine according to the patent of the Russian Federation for the invention No. 2320889, IPC F02K 3/04, publ. 03/27/2008, which contains a fan, a high-pressure high-speed compressor, a multiplier, a steam-water heater (steam generator), an afterburner, a turboexpander with a heat and mass transfer apparatus. The engine also has a three-stage active-jet turbine, in which the third stage is radial-axial, the flow part of which passes into the critical supersonic section of the Laval nozzle, surrounded by a steam accumulator. The high-speed high-speed compressor is combined with a pressure increase of 60. The engine is designed for thrust of at least 150 tons with an air flow through the first circuit of 600 kg / s, through the second circuit - 1200 kg / s, the gas temperature in front of the turbine is 2000 K. The fan has the outer diameter of the blades of the first row is 4000 mm. Inside the housing of the Laval nozzle, atomic hydrogen injectors are installed to burn the unburned oxidizer. The disks of a high-pressure high-speed compressor are made combined - centrifugal pumps are added to the axial steps. The Laval nozzle is provided with a central body, through the openings of which a steam-air mixture is created, creating an external elastic “shell-pillow”, which allows changing the area of the critical section of the Laval nozzle through passage.

Disadvantages - low level of traction, relatively low specific parameters, such as specific fuel consumption, insufficient compression of the compressor.

Low specific parameters are explained by the fact that it is impossible to create a compressor with a compression ratio of more than 30 ... 40, due to the fact that the air temperature at the outlet of it exceeds 800 ° C. In addition, the energy potential of a gas turbine is not enough to drive a more powerful compressor due to the limitation of the temperature of the gases at the outlet of the turbine to a range of 1700 ... 1800 ° K, primarily due to a decrease in the resource of working blades of a gas turbine. The working blades of a gas turbine are on a large diameter, rotate at huge peripheral speeds, therefore, they are subject to significant centrifugal loads. The strength properties of materials with increasing temperature deteriorate.

Known hydrogen gas turbine engine according to patent FR No. 2687433, IPC F02R 3/12, publ. 08/20/1992, the prototype.

This hydrogen gas turbine engine comprises an air intake, a housing, a compressor with a compressor rotor having a shaft, a main combustion chamber mounted behind the compressor and connected to it by the air path, and a supersonic jet nozzle, in that between the compressor and the combustion chamber inside the air path connecting the compressor and a combustion chamber, a hydrogen turbine is installed, which has an input and output collectors, and a heat exchanger is installed behind the combustion chamber, the input of which is connected to the fuel line, and the outlet - with an inlet manifold of the hydrogen turbine outlet manifold hydrogen turbine connected through a duct to the main combustion chamber, the outlet of the heat exchanger has a second compressor, and between which the supersonic jet nozzle installed afterburner.

The disadvantage is the low energy capabilities of a hydrogen gas turbine engine at hypersonic speeds due to the non-use of the power of a hydrogen turbine.

Objectives of the invention: improving the energy performance of a hydrogen gas turbine engine at hypersonic speeds.

Achieved technical results: increased energy performance at hypersonic speeds: compression ratio of the compressor, engine traction and its specific characteristics.

The solution of these problems was achieved in a hydrogen gas turbine engine containing an air intake, a housing, a compressor with a compressor rotor having a shaft, a main combustion chamber installed behind the compressor and connected to it by the air path, and a supersonic jet nozzle, while between the compressor and the combustion chamber inside the air of the path connecting the compressor and the combustion chamber, a hydrogen turbine is installed, which has an input and output collectors, and a heat exchanger is installed behind the combustion chamber, the input of which connected to the fuel line, and the output to the inlet manifold of the hydrogen turbine, the outlet manifold of the hydrogen turbine is connected by a pipeline to the main combustion chamber, a second compressor is installed at the outlet of the heat exchanger, an afterburner is installed between the supersonic jet nozzle and the hydrogen turbine and the second compressor connected to the compressor rotor shaft.

The jet nozzle can be made supersonic. The air intake can be made with cooled fuel. The jet nozzle may be a cooled fuel.

The invention is illustrated in FIG. 1 ... 4, where:

in FIG. 1 shows a diagram of a hydrogen gas turbine engine,

in FIG. 2 shows a diagram of the air intake,

in FIG. 3 shows the rotor of a hydrogen turbine,

in FIG. 4 shows a supersonic jet nozzle.

The proposed technical solution (Fig. 1 ... 4) contains an air intake 1, a housing 2 compressor 3, an air duct 4, a main combustion chamber 5, a heat exchanger 6, a second compressor 7, an afterburner 8 and a jet nozzle 9. It is preferable to perform a supersonic nozzle 9. Compressor 3 includes a stator 10 and rotor 11. The main combustion chamber 5 contains a flame tube 12 and nozzles 13. The second compressor 7 contains a stator 14 and rotor 15. The afterburner 8 has an afterburner manifold 16. The shaft 17 connecting the rotors 11 and common to the engine is 15 compressors 3 and 7 and mounted on supports 18 and 19. Inside the air path 4 concentric to the shaft 17 is installed a hydrogen turbine 20 operating on superheated hydrogen. The hydrogen turbine 20 has an outer diameter smaller than the inner diameter of the air path 4 so as not to clutter it. In addition, the small diametrical dimensions of the hydrogen turbine 20 reduce the centrifugal load on its rotating parts. The hydrogen turbine 20 contains a stator 21, a rotor 22, input and output collectors, 23 and 24, respectively (Fig. 1 and 3). In FIG. 3 shows in more detail the construction of the rotor 22 of the hydrogen turbine 20. The rotor 22 comprises a housing 25 in a villa of a hollow truncated housing 26, to which end walls 27 and 28 are connected, having coaxial spline bushings 29 and 30. The spline bushings 29 and 30 are in contact with splines 31 and 32, made on the shaft 17. On the housing 25 installed working blades 33.

The hydrogen gas turbine engine (Fig. 1) contains a fuel supply system having a tank 35 for storing hydrogen, a low pressure fuel line 36 connected to the outlet of the tank 35. The main and afterburning fuel lines 37 and 38 are connected to the low pressure fuel line 36.

The main fuel line 37 contains a pump 39, a flow regulator 40, and a shut-off valve 41. The bypass pipelines 42 and 43 respectively connect a heat exchanger 6 with an inlet manifold 23 of a hydrogen turbine 20 and an output manifold 24 with a main combustion chamber 5. The afterburner 38 contains a pump 44, a flow regulator 45 and a shut-off valve 46 installed in front of the afterburner manifold 16.

It is possible to make an air intake 1 with cooled fuel (Fig. 2), for this purpose its body 47 is made with an annular cavity 48, to which a main fuel pipe 37 and a pipe 49 connecting the annular cavity 48 to the inlet of the heat exchanger 6 are connected.

Perhaps the use of a cooled fuel (hydrogen) jet nozzle 9 (Fig. 4). For this, the outer and inner walls 50 and 51 are made with a gap 52 between them. The inlet and outlet manifolds 53 and 54 are installed on the outer wall 50. An afterburner fuel line 38 is connected to the inlet manifold 53, and a pipeline 55 is connected to the outlet manifold 54, the outlet of which is connected to the afterburner collector 16.

ENGINE OPERATION

When a hydrogen gas turbine engine is running, it is started by supplying electricity to the starter from an external energy source (in Fig. 1 ... 4 the starter and the energy source are not shown). Then they turn on the pump 39 and hydrogen from the tank 35 through the main fuel line 37 is supplied to the heat exchanger 6, then to the inlet manifold 23 of the hydrogen turbine 20, from the output manifold 24 through the bypass pipe 43 to the molds 13 of the main combustion chamber 5, where it is ignited using an electric igniter (on Fig. 1 ... 4 electric igniter is not shown). The rotor 22 of the hydrogen turbine 20 spins and spins through the shaft 17 the rotors 11 and 15 of the compressors 3 and 7. The compressor 3 provides a compression ratio of up to 30 ... 40, while the air temperature at its outlet can reach 800K. When burning fuel in the main combustion chamber 5, the temperature of the exhaust gas rises to 1800 ... 2000 ° C. In the heat exchanger 8, the combustion products are cooled to 300K. This is technically feasible due to the high heat capacity of hydrogen and its good heat transfer. The second compressor 7 additionally compresses the exhaust stream, creates a high pressure in the afterburner 8, which ensures the efficient operation of the nozzle 9, including supersonic.

If forcing is necessary, the shut-off valve 46 is opened and hydrogen is fed through the afterburner 38 to the afterburner 16, where it ignites and exhaust gases flow out of the jet nozzle 9, creating significant thrust comparable to the thrust of a liquid-propellant rocket engine of the same dimension. The use of heat exchanger 6, as noted earlier, will reduce the temperature of exhaust gases from 1800 ... 2000K to a temperature of 300K in front of the second compressor 7, which will allow the second compressor 7 to provide compression of the combustion products to 100 ... 150 kgf / cm ² , i.e. to a pressure commensurate with the pressure in modern rocket engines. Without pre-cooling, the second compressor 7 would in principle be inoperative. The high pressure in the afterburner 18 allows for the expiration of combustion products from the jet nozzles 9 with supersonic speeds, thereby creating a large jet thrust. Very high thrust with small engine dimensions allows aircraft equipped with such an engine to reach speeds M = 5 ... 10 and significantly increase the altitude of the engine.

The implementation of the hydrogen turbine 20 and the second compressor 7, connected with the shaft 17 of the rotor 11 of the compressor 3 allowed to increase energy performance in hypersonic modes: the compression ratio of the compressor, the engine traction force and its specific characteristics. This is because the main load for the drive of the second compressor 7 is assumed by the hydrogen turbine 20, which has a particularly high power at hypersonic speeds.

Regulation of traction in the afterburner mode is carried out by the flow regulator 40, in the afterburner mode by the flow regulator 45.

When the hydrogen gas turbine engine is stopped, all operations are carried out in the reverse order, i.e. shut-off valves 41 and 46 are closed.

The application of the invention allowed:

1. Due to the implementation of a hydrogen turbine and a second compressor, connected with the compressor rotor shaft, it allowed to increase energy performance in hypersonic modes: the compression ratio of the compressor, the engine traction force and its specific characteristics.

2. To increase the compression ratio of the compressors of the gas turbine engine through the use of two compressors and a turbine operating on hydrogen, and cooling the combustion products in front of the second compressor. The hydrogen turbine has small diametrical dimensions, so less centrifugal forces act on its working blades. The use of pure hydrogen as a working fluid significantly increases the energy potential of this working fluid. In addition, hydrogen can be heated to almost any temperature, which is limited only by the strength of the working blades of a hydrogen turbine operating in lighter conditions than the working blades of a gas turbine.

3. Ensure that aircraft equipped with these engines achieve hyperskuk speeds of M = 5 ... 0.

4. Increase engine altitude.

5. Increase engine reliability.

Claims (4)

1. A hydrogen gas turbine engine containing an air intake, a housing, a compressor with a compressor rotor having a shaft, a main combustion chamber mounted behind the compressor and connected to it by the air path, and a supersonic jet nozzle, characterized in that between the compressor and the combustion chamber inside the air path connecting the compressor and the combustion chamber, a hydrogen turbine is installed, which has an input and output collectors, and a heat exchanger is installed behind the combustion chamber, the input of which is connected to the fuel water, and the outlet - with the input manifold of a hydrogen turbine, the output manifold of a hydrogen turbine is connected by a pipeline to the main combustion chamber, a second compressor is installed at the outlet of the heat exchanger, an afterburner is installed between it and a supersonic jet nozzle, and the hydrogen turbine and the second compressor are connected to the shaft compressor rotor. 2. A hydrogen gas turbine engine according to claim 1, characterized in that the jet nozzle is made supersonic. 3. A hydrogen gas turbine engine according to claim 1 or 2, characterized in that the air intake is made of cooled fuel. 4. A hydrogen gas turbine engine according to claim 1, characterized in that the jet nozzle is made of cooled fuel.

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