RU2561772C1 - Air-jet engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: air-jet engine contains an air intake, a casing, a compressor with a compressor rotor, and a combustion chamber, a gas turbine, a shaft connecting the compressor and the gas turbine, and a jet nozzle. After the compressor an air channel is made, in it a first hydrogen-air heat exchanger is installed. Inside the air channel coaxially with the shaft the hydrogen turbine is installed, it has input and output headers. The input header is connected with the heat exchanger output, and the output header is connected with the combustion chamber. After the air channel a MP compressor and a HP compressor are installed, between them the second hydrogen-air heat exchanger is installed. Before the gas turbine the HP gas turbine is installed. The hydrogen turbine and MP compressor are connected by the second shaft, installed coaxially with the first shaft, and the HP compressor is connected with the HP turbine by the third shaft.

EFFECT: invention increases energetic capacities of the gas-turbine engine, improves the compression ratio of the compressor, thrust force of the engine and improves its specific characteristics.

2 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 (prototype), 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 its outlet 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 with 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.

Objectives of the invention: increasing the energy capabilities of a gas turbine engine and improving its specific characteristics.

Achieved technical results: increasing the compression ratio of the compressor, increasing the traction force of the engine and improving its specific characteristics.

The solution of these problems was achieved in an air-jet engine containing an air intake, a housing, a compressor with a compressor rotor and a combustion chamber, a gas turbine, a shaft connecting the compressor and a gas turbine, and a jet nozzle, characterized in that the air path is arranged behind the compressor, in which a first hydrogen-air heat exchanger is installed, a hydrogen turbine is installed coaxially to the shaft inside the air duct, which has an input and output collectors, an input collector is connected to the output of the heat exchanger and the output - with a combustion chamber, with a medium pressure compressor and a high pressure compressor installed between the air duct, a second hydrogen-air heat exchanger installed between them, a high-pressure gas turbine installed in front of the gas turbine, a hydrogen turbine and a medium pressure compressor connected by a second shaft mounted coaxially the first, and the high-pressure compressor is connected to the high-pressure turbine by a third shaft.

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 a hydrogen turbine,

- in FIG. 3 shows a series connection diagram of hydrogen-air heat exchangers,

- Fig. 4 shows a diagram of the parallel connection of hydrogen-air heat exchangers.

The proposed solution (Fig. 1 ... 4) contains an air intake 1, housing 2, compressor 3, air duct 4, a first hydrogen-air heat exchanger 5, a medium-pressure compressor 6, a second hydrogen-air heat exchanger 7, a high-pressure compressor 8, a combustion chamber 9, a gas turbine high pressure 10, a gas turbine 11 and a jet nozzle 12. The jet nozzle 12 is preferably supersonic.

The compressor 3 contains a stator 14 and a rotor 15. The medium-pressure compressor 6 contains a stator 16 and a rotor 17. The high-pressure compressor 8 contains a stator 18 and a rotor 19. The combustion chamber 9 contains a flame tube 20 and nozzles 21. The high-pressure gas turbine 10 contains a stator 22 and a rotor 23. The gas turbine 11 includes a stator 24 and a rotor 25. The shaft 26 connects the rotors 15 and 25 of the compressor 3 and the gas turbine 11 and is mounted on the supports 27 and 28. Inside the air path 4 concentric to the shaft 26 is installed a hydrogen turbine 29 operating on superheated hydrogen. The hydrogen turbine 29 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 29 reduce the centrifugal load on its rotating parts. The hydrogen turbine 29 includes a stator 30, a rotor 31, input and output collectors 32 and 33, respectively (Fig. 1 and 2).

In FIG. 2 shows the construction of the hydrogen turbine 29 in more detail. The stator 30 includes a housing 34 with end caps 35 and 36, on which the input manifolds 32 and the output manifold 33, respectively, are located. On the end caps 35 and 36 under the collectors 33 and 32, holes 37 and 38 are made.

The rotor 31 comprises a housing 39 in the form of a hollow truncated housing, to which the end walls 40 and 41 are connected. A sleeve 42 is connected to the end wall 40, and the second shaft 43 is connected to the end wall 41. The second shaft 43 connects the rotors 31 and 17 of the hydrogen turbine 27 and medium-pressure compressor 6. Nozzle vanes 44 are installed on the housing 32 on the inside 32, and rotor vanes 45 are installed on the outside of the rotor 31 on the housing 39. The rotor 31 is mounted on supports 46 and 47 and sealed relative to the stator 30 by seals 48, 49 and 50, 51.

A third shaft 52 connects the rotors 19 and 23 of the high pressure compressor 8 and the high pressure turbine 10, respectively.

The jet engine (FIG. 1) comprises a fuel supply system 52 having a hydrogen storage tank 53, a low pressure fuel pipe 54 connected to the outlet of the tank 53. A pump 55, a high pressure fuel pipe 56, a flow regulator 57 are connected to the low pressure pipe 54 and shut-off valve 58. Bypass pipelines 59 ... 61 respectively connect a second hydrogen-air heat exchanger 7 with an entrance to the first hydrogen-air heat exchanger 5, an exit from the first hydrogen-air heat exchanger 5 with an inlet manifold 32 of water one turbine 29 and outlet manifold 32 with the combustion chamber 9.

Hydrogen-air heat exchangers 5 and 7 can be connected in series (Fig. 1 and 3) or in parallel (Fig. 4). In the second embodiment, the entrances to the hydrogen-air heat exchangers 5 and 7 are connected using a pipe 62 to which a high-pressure fuel pipe 56 is connected. The exits from the hydrogen-air heat exchangers 5 and 7 are connected by a pipe 63 to which a pipe 61 is connected.

Possible execution of the jet nozzle 12 supersonic. This is suitable for supersonic aircraft.

ENGINE OPERATION

When the jet engine is operating (FIGS. 1 and 2), it is started by supplying electric power to the starter from an external energy source (in FIGS. 1 and 2, the starter and power source are not shown). Then they turn on the pump 55 and hydrogen from the tank 53 is fed into the second hydrogen-air heat exchanger 7, then through the bypass pipe 49 to the inlet manifold 26 of the hydrogen turbine 23, then from the output manifold 27 through the bypass pipe 50 to the nozzles 13 of the combustion chamber 8, where it is ignited using the ignition device (in Figs. 1 and 2, the ignition device is not shown). The rotor 31 of the hydrogen turbine 29 spins and spins through the second shaft 43 the rotor 15 of the second compressor 6. The rotor 11 is driven by the rotor 19 of the gas turbine 8 through the shaft 20. Compressor 3 provides a compression ratio of up to 30 ... 40, while the air temperature at its output can reach 800 K. It is next to impossible to compress such hot air in the compressor further. In the air path 4, the air is cooled to 300 ... 400 K and becomes again suitable for compression. During the combustion of fuel (hydrogen) in the combustion chamber 9, the temperature of the exhaust gas rises to 1800 ... 2000 ° C. A gas having a high temperature and pressure has a significant energy potential for its operation on gas turbines 10 and 11 and to ensure the effective operation of the jet nozzle 12.

The use of two hydrogen-air heat exchangers 5 and 7, as noted earlier, will reduce the air temperature at the outlet from 700 ... 800 K to a temperature of 250 ... 300 K in front of medium and high pressure compressors 6 and 8, which will allow both compressors 6 and 8 in conjunction with compressor 3 to provide compression of the combustion products to 100 ... 150 kgf / cm ² (in terrestrial conditions), i.e. to a pressure commensurate with the pressure in modern rocket engines. Without pre-cooling, medium and high pressure compressors 6 and 8 would in principle be inoperative. The high pressure in front of the combustion chamber 9 allows for a pressure drop across the gas turbines 10 and 11 and the expiration of the combustion products from the jet nozzle 12 at supersonic speeds, thereby creating a large jet thrust. Very high thrust with small engine dimensions allows you to reach aircraft equipped with such an engine speed M = 5 ... 10 and significantly increase the altitude of the engine.

Traction control is provided by a flow regulator 57.

When the jet engine is stopped, all operations are carried out in the reverse order, i.e. close the shut-off valve 58.

The application of the invention allowed:

1. To increase the compression ratio of the gas turbine engine compressors through the use of three compressors, two gas turbines and a hydrogen turbine, as well as cooling of 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. The compression ratio of the compressors can be increased through the use of two hydrogen-air heat exchangers installed between them.

2. Ensure that aircraft equipped with these engines achieve hypersonic speeds M = 5 ... 10.

3. Increase the height of the engine due to the greater productivity of the three compressors.

4. Increase engine reliability due to the small size of the hydrogen turbine and reduce centrifugal loads on its blades.

Claims (2)

1. An air-jet engine containing an air intake, a housing, a compressor with a compressor rotor and a combustion chamber, a gas turbine, a shaft connecting the compressor and a gas turbine, and a jet nozzle, characterized in that an air path is provided behind the compressor, in which the first hydrogen-air a heat exchanger, a hydrogen turbine is installed coaxially to the shaft inside the air duct, which has an inlet and an outlet manifold, the inlet manifold is connected to the outlet of the heat exchanger, and the outlet to the combustion chamber, for this, a medium-pressure compressor and a high-pressure compressor are installed behind the air duct, between which a second hydrogen-air heat exchanger is installed, a high-pressure gas turbine is installed in front of the gas turbine, a hydrogen turbine and a medium-pressure compressor are connected by a second shaft mounted coaxially to the first, and a high-pressure compressor is connected to the high-pressure turbine third shaft pressure. 2. The jet engine according to claim 1 or 2, characterized in that the jet nozzle is made supersonic.

Images