RU2791941C1 - Hypersonic aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aviation. A hypersonic aircraft contains a fuselage, wings, fuel tanks, direct-flow engines, rocket engines and fuel component pipelines. Propeller gas turbine engines are installed on wings. Rocket engines are designed to run on oxidizer and propellant in the form of liquid oxygen and liquid hydrogen. The fuselage contains an oxidizer tank and tanks with first and second fuel. Oxidant piping goes inside first and second fuel tanks and is connected by pipelines to all rocket engines. The direct-flow engines are installed in wings and connected to the first propellant tank via fuel pipelines. The propeller gas turbine engines are desgined as three-shaft engines containing two propeller stages in the front part, have no gearbox with magnetic couplings between the turbocharger shafts and the propeller stages. The rocket engines are designed to rotate and lock in the vertical plane. The direct-flow engines are equipped with pivoting dampers for pitch control. Oxidizer and propellant pipelines are thermally insulated.

EFFECT: invention provides for increasing aircraft speed and efficiency.

6 cl, 8 dwg

Description

The invention relates to aviation, namely to hypersonic aircraft and can be used for space bombers.

Known supersonic aircraft according to the RF patent for invention No. 20101744, IPC V84S 39/10, publ. 04/15/1994 The aircraft body is made in any longitudinal section along a cubic parabola with a blunt aft part and a sweep angle along the leading edge of at least 60°. The elevator is made in the form of a hinged front part of the body.

The disadvantage is the relatively low speed of the aircraft M=3…5. The aircraft cannot develop hypersonic speeds.

Known supersonic aircraft according to the RF patent for invention No. 2130407, IPC V64C 39/02, publ. 05/10/1999, containing the fuselage, wings, starting and marching propulsion systems. Starting propulsion systems are made in the form of gas turbine engines - gas turbine engines, and main engines - in the form of ramjet engines, specifically in the patented development it is proposed to use pulsed detonation jet engines.

The disadvantages of this aircraft are the relatively low flight speed of the aircraft and the long time it takes to accelerate to hypersonic speeds due to the low thrust of the gas turbine engine.

Known hypersonic aircraft according to the RF patent for invention No. 2305056, IPC B64D 37/06, publ. 08/27/2007, prototype.

This hypersonic aircraft contains a fuselage, wings, fuel tanks, propulsion ramjet engines, starting rocket engines. Starting rocket engines are made on liquid fuel components. In the fuselage tanks with oxidizer and fuel are installed.

Prototype Disadvantages:

- a relatively low flight speed of a hypersonic aircraft and a long time for its acceleration to hypersonic speeds due to the low thrust of the starting rocket engines and their low efficiency due to the consumption of an oxidizer from their own reserves.

- the impossibility of using marching ramjet engines in space, for example, for space bombers.

The tasks of creating a hypersonic aircraft: reducing the time it takes for an aircraft to accelerate to hypersonic speeds and increasing the aircraft's flight speed.

The solution of these problems is achieved due to the fact that a hypersonic aircraft containing a fuselage, wings, fuel tanks and engines, including ramjet engines and rocket engines and pipelines for supplying fuel components to them, by the fact that propfan gas turbine engines are additionally installed on the wings of the aircraft, rocket engines are made to operate on liquid fuel components: an oxidizer and fuel in the form of liquid oxygen and liquid hydrogen, a tank with an oxidizer and tanks with the first and second fuels are installed in the fuselage, the oxidizer supply pipeline runs inside the first and second fuel tanks, and the fuel tank is connected by pipelines supply of the second fuel with all rocket engines, direct-flow engines are made in the wings and are connected by fuel pipelines to the first fuel tank.

Propfan gas turbine engines can be made according to a three-shaft scheme and contain two propfan stages in the front of these engines.

Propfan gas turbine engines can be made without a gearbox with magnetic couplings between the turbocharger shafts and propfan stages.

Rocket engines can be made with the possibility of rotation and fixation in a vertical plane.

The output ramjet engines can be equipped with butterfly valves for pitch control.

Pipelines for supplying oxidizer and fuel can be thermally insulated.

The proposed technical solution has novelty, inventive step and industrial applicability. The novelty is confirmed by the conducted patent research, and the inventive step is confirmed by the fact that a new set of essential features made it possible to obtain a new technical effect, namely, a reduction in the acceleration time of an aircraft to hypersonic speeds and an increase in flight speed. Industrial applicability is due to the fact that the implementation of the invention does not require the creation of new parts and assemblies unknown from the prior art and new technologies.

The essence of the invention is illustrated in Fig. 1…8, where:

in fig. 1 shows a diagram of a hypersonic aircraft,

in fig. 2 - diagram of a ramjet engine,

in fig. 3 - diagram propfan gas turbine engine, VVGD,

in fig. 4 - scheme of the rocket engine,

in fig. 5 shows a sectional view of the second magnetic coupling,

in fig. 6 shows a sectional view of the first magnetic coupling,

in fig. 7 shows the disk assembly with the leading magnets,

in fig. 8 shows the disk assembly with driven magnets,

Essential features used in the description

1 - fuselage 1,

2 - stabilizers 2,

3 - wings 3,

4 - rocket engines 4,

5 - direct-flow motors 5

6 - oxidizer tank 6,

7 - first fuel tank 7,

8 - oxidizer supply pipeline 8,

9 - pipeline of the second fuel 9,

10 - fuel pipeline 10,

11 - air intake 11,

12 - propfan gas turbine engine 12,

13 - expanding supersonic nozzle 13.

14 - fuel manifold 14,

15 - hinge 15

16 - controlled sashes 16,

17 - rods 17,

18 - control cylinder 18,

19 - connections 19,

20 - control unit 20.

21 - combustion chamber 21,

22 - turbopump unit 22,

23 - THA 23 shaft,

24 - impeller of the oxidizer pump 24,

25 - impeller of the fuel pump 25,

26 - starting turbine 26,

27 - additional fuel pump 27,

28 - shaft of additional fuel pump 28,

29 - multiplier 29,

30 - building 30

31 - main turbine 31,

32 - gas generator 32

33 - nozzle 33

34 - gap 34,

35 - head of the combustion chamber 35,

36 - outer plate 36

37 - inner plate 37

38 - cavity between plates 38,

39 - oxidizer nozzles 39.

40 - nozzles of the second fuel 40,

41 - purge pipeline 41,

42 - the cavity of the chamber 42,.

43 - oxidizer fuel line 43,

44 - oxidizer valve 44.

45 - main collector of the second fuel 45,

46 - high pressure fuel line 46,.

47 - flow regulator 47,

48 - regulator drive 48..

49 - high pressure valve 49,

50 - intermediate cavity 50,

51 - pipeline of the second fuel 51,

52 - valve of the second fuel 52,

53 - the cavity of the generator 53,

54 - ignition devices of the camera 54,

55 - ignition devices of the generator 55.

56 - high pressure pipeline 56,

57 - starting valve 57,

58 - purge pipeline 58,

59 - purge valve 59.

60 - pins 60,

61 - hydraulic cylinder 61,

62 - turbocharger 62,

63 - the first stage of the propfan 63,

64 - second stage propfan 64,

65 - blades 65,

66 - first shaft 66,

67 - second shaft 67,

68 - third shaft 68,

69 - the first compressor 69,

70 - second compressor 70,

71 - main combustion chamber 71,

72 - the first turbine 72,

73 - second turbine 73,

74 - third turbine 74

75 - exhaust device 75.

76 - low pressure fuel line 76,

77 - fuel pump 77,

78 - pump drive 78,

79 - high pressure fuel line 79,

80 - ring manifold 80,

81 - nozzles 81,.

82 - supports 82,

83 - building 83,

84 - guide vanes of the first compressor 84,

85 - working blades of the first compressor 85,

86 - guide vanes of the second compressor 86,

87 - working blades of the second compressor 87,

88 - nozzle apparatus of the first turbine 88,

89 - nozzle apparatus of the second turbine 89,

90 - nozzle apparatus of the third turbine 90,

91 - working blades of the first turbine 91,

92 - rotor blades of the second turbine 92,

93 - rotor blades of the third turbine 93,

94 - magnetic clutch 94

95 - the first output shaft 95,

96 - second output shaft 96,

97 - fairing 97

98 - second circuit 98,

99 - front of the engine 99,

100 - casing 100,

101 - disk 101,

102 - leading coupling half 102,

103 - driving magnets 103,

104 - driven coupling half 104,

105 - driven magnets 105.

106 - front part of the third shaft 106,

107 - front part of the second shaft 107,

108 - stops 108,

109 - second fuel tank 109,

110 - Payload 110.

The main feature of the proposed hypersonic aircraft (Fig. 1) is the presence of three types of engines: direct-flow 5, propfan 12 and rocket 4.

Hypersonic aircraft (Fig. 1) contains a fuselage 1, stabilizers 2, wings 3, rocket engines 4, direct-flow engines 5 installed in the wings 3, an oxidizer tank 6 (liquid oxygen), a first fuel tank 7 (kerosene). The oxidizer tank 6 is connected by an oxidizer supply pipeline 8 to rocket engines 4. The second fuel tank 109 is connected by a fuel pipeline 9 to rocket engines 4. The first fuel tank 7 (kerosene) is connected to ramjet engines 5 by fuel pipelines 10.

A diagram of a ramjet 5 intended for flight in the upper atmosphere is shown in Fig. 2.

SCHEME AND OPERATION OF THE DIRECT-FLOW MOTOR

Direct-flow engines 5 are built into the wings 3 of the aircraft and contain an air intake 11 of a confused shape, a narrowing-expanding supersonic nozzle 13. A fuel manifold 14 is installed inside the main ramjet engines 5, which is connected by a fuel pipeline 10 to the first fuel tank 7. At the upper exit edge of the wings 3 on the hinge 15 is fixed to the controlled flaps 16, to which the rods 17 of the control cylinders 18 are connected, which are connected by links 19 to the control unit 20.

DIAGRAM AND OPERATION OF THE PROPELLER ENGINE

Propeller gas turbine engine 12 is designed for takeoff and climb in dense layers of the atmosphere (up to 11 km).

The propfan gas turbine engine 12 (Fig. 4) contains a three-shaft turbocharger 62 with the first 66, second 67 and third 68 shafts and two propfan stages 63 and 64 having blades 65.

Such a scheme is typical for the NK 93 engine. Kuznetsov and they can actually be used in the project.

The design of the NK 93 engine can be finalized and a more modern engine without a gearbox with magnetic couplings (Fig. 4) can be manufactured, which has better characteristics.

The propfan gas turbine engine 12 in both versions contains two compressors 69 and 70 and three turbines: 72-74 and the main chamber 71.

The propfan stages 63 and 64 are installed in front of the engine 99 in both circuits, including the second circuit 98, and are connected to the front of the third shaft 106 and the front of the second shaft 107. The drive coupling halves 101 are connected to the first output shaft 95 and the second output shaft 96, on which propfan stages 63 and 64 are installed.

The turbocharger 62 includes two compressors 68 and 69, a main combustion chamber 71 and three turbines 72-74 and an exhaust device 75. The turboprop gas turbine engine (Fig. 1) contains a fuel supply system with a low pressure fuel line 76 connected to the inlet to the fuel pump 77, having a pump drive 78, a high-pressure fuel line 79, the inlet of which is connected to the fuel pump 77, and the outlet is connected to the annular manifold 80. The annular manifold 80 is connected to the injectors 81 of the main combustion chamber 71.

The first compressor 69 includes the guide vanes of the first compressor 84 and the rotor blades of the first compressor 85. The second compressor 70 includes the guide vanes of the second compressor 85 and the rotor blades of the second compressor 87

The first turbine 72 contains the first stage nozzles of the turbine 88 and the rotor blades of the first turbine 91.

The second turbine 73 contains the nozzle apparatus of the second turbine 89 and the rotor blades of the second turbine 92.

The third turbine 74 contains the nozzle apparatus of the third turbine 90 and the rotor blades of the third turbine 93.

All shafts of the three-shaft engine 66-68 are mounted on supports 82 and the entire turbocharger 62 has a housing 83. An exhaust device 75 is installed behind the turbines 72-74

In front of the turbocharger 62, two stages of the propfan 63 and 64 are installed. The propfan is a device for pumping (compressing) air, it occupies an intermediate position between a propeller and a fan. In relation to aircraft engines, a screw is a device having from 2 to 4 blades. The fan has a significant number of blades from 14 to 50 or more, i.e. it practically does not differ from the axial compressor. The propfan has from 5 to 13 blades. The use of a propeller makes it possible to create an aircraft engine that is highly economical, but due to its large diameter it has limitations in flight speed and creates a high level of noise. A bypass engine with a fan makes it possible to design a gas turbine engine for flights at supersonic speeds, but is significantly inferior in terms of efficiency to engines with propellers, for example, turboprop gas turbine engines. The use of propfans is the latest trend in aircraft engine building and will allow combining the positive properties of the two types of aircraft engines described above and eliminating all disadvantages.

Propellers 63 and 64 are connected to the third and second shafts 68 and 67 by means of two magnetic couplings 94 (first and second couplings), see FIG. 4.

Shafts third 68 and second 67 contain the front part of the third shaft 106, the front part of the second shaft 107, for attaching magnetic couplings 94 or rather their drive halves 102.

This design of the magnetic coupling 94 made it possible to increase its power due to the location of the magnets on a large number of disks 101. This is especially important for powerful aircraft engines, in which it is necessary to transmit power of 10 ... 20 MW.

It is possible to use an engine scheme with two propfan stages 63 and 64, which can rotate in opposite directions. In this version of the engine, the compressor is made as a two-stage compressor, i.e. contains a low-pressure compressor rotor and a high-pressure compressor rotor, respectively, with an internal shaft and an external shaft not connected kinematically to each other. Shafts 66 and 67 are designed so that they always rotate in opposite directions during operation. This is achieved due to different installation angles of the guides and rotor blades in both compressor stages. The opposite rotation of the two shafts reduces the reactive moment acting on the wing of the aircraft and the gyroscopic effect that creates radial loads on the engine bearings.

The propfan stages 63 and 64 can be installed inside the fairing 97. This will eliminate the radial overflow of air and increase the efficiency of the propfan gas turbine engine 12 (VVGD). In addition, the 97 fairing significantly reduces engine noise.

VVGD 12 contains a three-shaft turbocharger 62 with the first 66, second 67 and third 68 shafts and two propfan stages 63 and 64 having blades 65.

The design of the magnetic couplings 94 is shown in more detail in FIG. 5-7.

Magnetic clutches 94 are made inside the casing 100, and consist of disks 101, which form a driving half-coupling 102 with driving magnets 103 and a driven half-coupling 104 with driven magnets 105. The driving half-couplings 102 are mounted rigidly on the front part of the third shaft 106 and the front part of the second shaft 107. The output of the transmitted torque is carried out on the first output shaft 95 and the second output shaft 96 with the driven coupling halves rigidly fixed on them. 104. In FIG. 7 and 8 show the disks 101 of the leading coupling halves. 102 and driven coupling halves. 104.

Stops 108 are used to transfer axial forces.

SCHEME AND OPERATION OF THE ROCKET ENGINE

Rocket engines 4 (Fig. 3) are designed to accelerate rockets in space to hypersonic speeds M=12-15. It runs on liquid hydrogen and oxygen.

Rocket engine 4 (Fig. 4) contains a combustion chamber 21 and a turbopump unit 22. The turbopump unit 22, in turn, contains an oxidizer pump impeller 24, an impeller of a fuel pump 25, a starting turbine 26, an additional fuel pump 27, mounted on the TNA shaft 23, with an additional fuel pump shaft 28 connected by a multiplier 29 placed in a housing 30 with a THA shaft 23, the main turbine 31 is made in the upper part of the turbopump unit 22. The gas generator 32 is installed above the main turbine 31 coaxially with the turbopump unit 22. The combustion chamber 21 contains a nozzle 33, made of two shells and a gap 34 between them, and the head of the combustion chamber 35, inside which the outer plate 36 and the inner plate 37 are made with a cavity 38 between them. Inside the head of the combustion chamber 35, oxidizer nozzles 39 and second fuel nozzles 40 are installed. of which the fuel lines of the second fuel depart to the lower part of the nozzle 33. The outlet of the second fuel valve 52 is connected to the fuel manifold 45, the inlet of which is connected by the second fuel line 51 to the outlet of the impeller of the fuel pump 25. The outlet of the additional fuel pump 27 is connected by a high pressure fuel line 46 through flow regulator 47, having a regulator drive 48 and a high pressure valve 49 with a gas generator 32, specifically with a cavity 53.

The outlet from the impeller of the oxidizer pump 24 is also connected by the oxidizer pipeline 43 through the valve 44 to the gas generator 32, specifically to the cavity of the gas generator 53. The ignition devices of the chamber 54 are installed on the head 35 of the combustion chamber 21, and the ignition devices of the gas generator 55 are installed on the gas generator 31.

To the starting turbine 26, a high-pressure pipeline 56 with a starting valve 57 is connected, designed to start the starting turbine 26.

Ignition devices 54 and 55, high pressure valve 49, oxidizer valve 53, flow regulator drive 48, high pressure valve 49, starting valve 57 are connected to the control unit 20 by electrical connections 19.

A purge pipeline 58 with a purge valve 59 is connected to the fuel manifold 43. Pins 60 are made on the combustion chamber 21 for its swing in one plane. The drive is carried out using a hydraulic cylinder 61 connected to the control unit 20.

In FIG. 1 shows a second fuel tank 109 (which is liquid hydrogen) and a payload 110, such as an atomic bomb.

HYPERSONIC AIRCRAFT WORK

During the operation of propfan gas turbine engines 12, they are started by supplying electricity to the starter from an external energy source (the starter is not shown in Fig. 1...7). Then the drive of the fuel pump 7 is turned on, and the fuel pump 77 supplies fuel to the main combustion chamber 71, more precisely to the injectors 81, where it is ignited using an electric igniter (the electric igniter is not shown in Fig. 1 ... 7). Shafts 67 and 68 spin up and spin the propfan stages 62 and 63. The external power source is turned off.

Approximate characteristics of a hypersonic aircraft:

Airspeed M=10 Starting weight, t 250 Thrust of rocket engines, t 2×150 Thrust of ramjet engines, t 6×20 Acceleration time М=12-15, s 100

Rocket fuel components for LRE

Oxidizer oxygen Fuel hydrogen Fuel for a marching ramjet engine kerosene Fuel for propfan engines kerosene Thrust of propfan engines, t 2×30 Thrust propfan engines, second option, t 4×30

The inclusion of ramjet engines 5 is carried out in low-density layers of the atmosphere at a flight altitude of 11 km - 30 km

To do this, the first fuel from the first fuel tank 7 through the fuel pipeline 10 is supplied by a fuel pump (not shown in Fig. 1-7) to the fuel manifold 14 of ramjet engines 5. When the fuel is burned, energy is released, and the resulting exhaust gases enter the expanding supersonic nozzle 13 and beyond go into the atmosphere, creating jet thrust.

When accelerating a hypersonic aircraft, the flight angles are controlled by mismatching the thrust of rocket engines 4 and swinging on pins 60 using hydraulic cylinders 61. In hypersonic mode, the aircraft is controlled by control unit 20 using controlled flaps 16, which are deflected by means of control hydraulic cylinders 18.

OPERATION OF ROCKET ENGINES

When rocket engines 4 (Fig. 4) are started, signals are sent from the control unit 20 to the starting valve 57. High-pressure air is supplied through the high-pressure pipeline 56 to the starting turbine 26 and spins the TNA rotor 22. The pressure of the oxidizer (oxygen) and the second fuel (hydrogen ) at the outlet of the impellers of the oxidizer pumps 22 and fuel 23 increases. A signal is given to open valves 44, 49 and 52. The oxidizer and the second fuel enters the combustion chamber 21 and the gas generator 32. A signal is given to the ignition devices 54 and 55, the fuel mixture in the combustion chamber 21 and in the gas generator 32 ignites, the rocket engine 4 starts. The flow controller 47 with the help of the regulator drive 48 regulates the mode of its operation.

When the rocket engines 4 are turned off, the control unit 20 sends a signal to the valves 44, 49 and 52, which close. Then a signal is given to open the purge valve 59 and the inert gas through the purge pipeline 41 enters the main fuel pipeline 46 and further into the gap 34 to remove the remnants of the second fuel (hydrogen).

The application of the invention allowed:

1. Increase the flight speed of a hypersonic aircraft to M = 12-15 through the use of hydrogen-powered rocket engines.

2. Accelerate the process of gaining maximum hypersonic speed through the use of three types of engines operating in different conditions.

3. Simplify the fuel supply scheme for starting and sustainer engines.

4. Improve the reliability of hypersonic aircraft.

5. Increase the power and specific characteristics of a hypersonic aircraft.

6. Reduce the weight of the aircraft, starting and ramjet engines by unifying one of the fuel components of the first fuel (kerosene) for two types of engines.

7. Ensure reliable control of a hypersonic aircraft in all modes of its operation.

8. Improve the starting and shutdown of engines and ensure their cleaning of fuel residues after shutdown.

Claims (6)

1. A hypersonic aircraft containing a fuselage, wings, fuel tanks and engines, including ramjet engines and rocket engines and pipelines for supplying fuel components to them, characterized in that propfan gas turbine engines are additionally installed on the wings of the aircraft, rocket engines are made running on components liquid fuel: oxidizer and fuel in the form of liquid oxygen and liquid hydrogen, a tank with an oxidizer and tanks with the first and second fuels are installed in the fuselage, the oxidizer supply pipeline runs inside the first and second fuel tanks, and the second fuel tank is connected by pipelines for supplying the second fuel to all rocket engines, direct-flow engines are made in the wings and are connected by fuel pipelines to the first fuel tank. 2. Hypersonic aircraft according to claim. 1, characterized in that propfan gas turbine engines are made according to a three-shaft scheme and contain two propfan stages in front of these engines. 3. Hypersonic aircraft according to claim. 2, characterized in that propfan gas turbine engines are made without a gearbox with magnetic couplings between the shafts and stages of the propfan. 4. Hypersonic aircraft according to claim. 1, characterized in that the rocket engines are made with the possibility of rotation and fixation in a vertical plane. 5. Hypersonic aircraft according to claim. 1, characterized in that the ramjet engines at the output are equipped with rotary dampers for pitch angle control. 6. Hypersonic aircraft according to claim 1, characterized in that the oxidizer and fuel supply pipelines are thermally insulated.

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