Common turbine fuel supply system with clutch for fuel precooling ATR

Abstract

The invention discloses a common turbine fuel supply system with a clutch for a fuel pre-cooling ATR, and the system comprises a fuel turbine which is driven by fuel to rotate; a fuel pump is mounted on the base; a driving disc of the clutch is installed on the fuel turbine, an oxidizing agent pump is installed on a driven disc of the clutch, and the clutch is used for driving the fuel pump and the oxidizing agent pump to rotate under the rotation of the fuel turbine in a closed state so as to provide power for flowing of fuel and an oxidizing agent; the fuel pump and the oxidant pump share the fuel turbine, whether the oxidant pump works or not is controlled through the clutch, the structure of the engine is simplified, and the mass of the engine is reduced.

Description

Technical Field

[0001] The invention belongs to the field of aerospace propulsion, and in particular relates to a common turbine fuel supply system with a clutch for a fuel precooling ATR. Background Art

[0002] The air turbine rocket engine (ATR) is a combined cycle air-breathing propulsion system that combines a turbine engine and a rocket engine. Its specific impulse is higher than that of a rocket engine, its thrust-to-weight ratio is higher than that of a turbine engine, and its thrust adjustment range is large, with moderate technical difficulty. During the operation of the ATR engine, as the flight Mach number increases, the total temperature of the incoming flow continues to rise, causing the cycle heating to gradually decrease, reducing the thrust output of the engine. At the same time, due to temperature limitations, the actual pressure ratio provided by the compressor continues to decrease, and the core engine contributes very little to the thrust at high Mach numbers, becoming the dead weight of the engine. Therefore, it is considered to use pre-cooling technology to cool the incoming flow, reduce the total temperature of the incoming flow, increase the air flow rate at high Mach numbers, and increase the pressure ratio, thereby improving the working performance of the engine and broadening its working speed range.

[0003] The ATR engine can use a variety of fuel systems. One way to precool the incoming air is to use the low-temperature fuel carried by the engine to exchange heat with the air. At this time, the fuel carried by the engine not only participates in the combustion reaction but also participates in the heat exchange as a precoolant. The fuel supply system is a key component of the engine. In the pump-pressure supply system, the fuel turbine and the oxidizer turbine are generally used to drive the fuel pump and the oxidizer pump respectively to supply fuel and oxidizer to the gas generator; or an electric motor is used to drive the fuel pump and the oxidizer pump. Such a fuel supply system has a relatively complex structure and a large mass, which increases the mass of the engine and limits the improvement of the thrust-to-weight ratio of the ATR engine. Summary of the invention

[0004] The purpose of the present invention is to provide a common turbine fuel supply system with a clutch for fuel precooling ATR, so as to solve the problem that the fuel supply system has a complex structure and a large mass, thereby limiting the improvement of the thrust-to-weight ratio of the ATR engine.

[0005] The present invention adopts the following technical solution: a common turbine fuel supply system with a clutch for a fuel precooling ATR, comprising:

[0006] A fuel turbine, used to rotate under the drive of fuel; a fuel pump is installed on the fuel turbine;

[0007] The clutch has an active plate mounted on the fuel turbine and an oxidant pump mounted on its driven plate. The clutch is used to drive the fuel pump and the oxidant pump to rotate under the rotation of the fuel turbine when in a closed state, thereby providing power for the flow of fuel and oxidant.

[0008] Furthermore, it also includes:

[0009] A precooler having an air flow path inlet, an air flow path outlet, a fuel flow path inlet, and a fuel flow path outlet;

[0010] Its air flow path inlet is connected to the air intake duct outlet;

[0011] Its air flow path outlet is connected to the compressor inlet;

[0012] Its fuel flow path inlet is connected to the outlet of the fuel pump;

[0013] The precooler is used to use the low-temperature fuel from the fuel pump to cool the high-temperature incoming air, so that the temperature of the incoming air is reduced before it is delivered to the compressor.

[0014] Furthermore, it also includes:

[0015] A combustion chamber having a gas inlet and an air inlet;

[0016] Its gas inlet is connected to the gas outlet of the ATR's main turbine;

[0017] Its air inlet is connected to the outlet of the compressor;

[0018] The combustion chamber is used for complete combustion of the rich fuel gas from the main turbine and the air from the compressor.

[0019] Furthermore, the middle part of the fuel pipeline between the precooler and the fuel turbine is arranged close to the combustion chamber, and is used to heat the fuel in the fuel pipeline by using the heat of the combustion chamber, so that the liquid fuel in the fuel pipeline is vaporized into gaseous fuel, and then enters the fuel turbine, and further includes:

[0020] A gas generator having a gas inlet, an oxidant inlet, and a gas outlet;

[0021] Its gas inlet is connected to the gas outlet of the fuel turbine;

[0022] Its gas outlet is connected to the gas inlet of the main turbine;

[0023] Its oxidant inlet is connected to the outlet of the oxidant pump;

[0024] The gas generator is used to drive the gas fuel of the fuel turbine to pre-react with the oxidant in the gas generator, and the pre-reacted gas is transported to the main turbine of the ATR.

[0025] The beneficial effects of the present invention are:

[0026] In the present invention, the fuel pump and the oxidant pump share a fuel turbine, and the clutch is used to control whether the oxidant pump is working, thereby simplifying the structure of the engine and reducing the weight of the engine.

[0027] The present invention uses a precooler to keep the compressor inlet air flow temperature constant or change only within an allowed range, thereby improving the working performance of the engine and widening the working speed range of the engine;

[0028] The present invention heats and vaporizes the liquid fuel in the fuel pipeline by cooling the combustion chamber wall, thereby reducing the difficulty of thermal protection of the combustion chamber and eliminating the need to provide a separate heat exchange device.

[0029] In the present invention, when the turbine mode clutch is closed, the fuel pump and the oxidant pump work simultaneously to provide fuel and oxidant to the gas generator. When the ramjet mode gas generator stops working, the clutch is disconnected to control the oxidant pump to stop working. At this time, only the fuel pump needs to work to provide fuel to the combustion chamber. If a solution of separately setting up a fuel turbine and an oxidant turbine is adopted, or a solution of separately setting up electric motors is adopted, the oxidant supply structure will become the "dead weight" of the engine in the ramjet mode. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the turbine modal thermodynamic cycle of the present invention;

[0031] Figure 2 It is a schematic diagram of the stamping modal thermodynamic cycle of the present invention.

[0032] Among them: 10. Fuel turbine; 11. Clutch; 12. Oxidant pump; 13. Fuel pump; 14. Precooler; 15. Combustion chamber; 16. Gas generator. DETAILED DESCRIPTION

[0033] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0034] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more. The "direction" in the present invention is based on the position of the present invention in a certain direction. Figure 1 Description of the trend in the state.

[0035] The present invention discloses a common turbine fuel supply system with a clutch for a fuel precooling ATR, such as Figure 1 The components shown include: a fuel turbine 10 and a clutch 11 .

[0036] The fuel turbine 10 is used to rotate under the drive of fuel; a fuel pump 13 is installed on the fuel turbine 10; the active plate of the clutch 11 is installed on the fuel turbine 10, and the oxidant pump 12 is installed on the driven plate thereof. The clutch 11 is used to drive the fuel pump 13 and the oxidant pump 12 to rotate under the rotation of the fuel turbine 10 when in a closed state, thereby providing power for the flow of fuel and oxidant.

[0037] The present invention also includes: a precooler 14, the precooler 14 has an air flow path inlet, an air flow path outlet, a fuel flow path inlet, and a fuel flow path outlet; the air flow path inlet of the precooler 14 is connected to the intake duct outlet; the air flow path outlet of the precooler 14 is connected to the inlet of the compressor; the fuel flow path inlet of the precooler 14 is connected to the outlet of the fuel pump 13; the precooler 14 is used to use the low-temperature fuel from the fuel pump 13 to cool the high-temperature incoming air, so that the temperature of the incoming air is reduced and then it is transported to the compressor.

[0038] The present invention also includes: a combustion chamber 15, the combustion chamber 15 has a gas inlet and an air inlet; the gas inlet of the combustion chamber 15 is connected to the gas outlet of the main turbine of the ATR; the air inlet of the combustion chamber 15 is connected to the outlet of the compressor; the combustion chamber 15 is used for the complete combustion of the fuel-rich gas from the main turbine and the air from the compressor.

[0039] The middle part of the fuel pipeline between the precooler 14 and the fuel turbine 10 is arranged close to the combustion chamber 15. After this arrangement, the heat of the combustion chamber 15 can be used to heat the fuel in the fuel pipeline, so that the liquid fuel in the fuel pipeline is vaporized into gaseous fuel, and then enters the fuel turbine 10 and drives the fuel turbine 10 to rotate.

[0040] The present invention also includes: a gas generator 16, the gas generator 16 has a gas inlet, an oxidant inlet, and a gas outlet; the gas inlet of the gas generator 16 is connected to the gas outlet of the fuel turbine 10; the gas outlet of the gas generator 16 is connected to the gas inlet of the main turbine; the oxidant inlet of the gas generator 16 is connected to the outlet of the oxidant pump 12; the gas generator 16 is used to drive the gas fuel and oxidant of the fuel turbine 10 to pre-react in the gas generator 16, and transport the pre-reacted gas to the main turbine of the ATR.

[0041] The present invention has two working modes:

[0042] The first working mode is the turbine mode, such as Figure 1 As shown, the specific working principle is as follows: the incoming air enters the intake duct, and the airflow at the outlet of the intake duct is controlled to flow to the compressor by controlling the switching valve. A precooler 14 is provided in front of the compressor to cool the incoming air. The low-temperature liquid methane in the fuel tank is pressurized by the fuel pump 13 and flows to the precooler 14. The low-temperature liquid methane and the high-temperature incoming air complete heat exchange in the precooler 14. In order to make methane obtain more heat and vaporize to drive the fuel turbine 10, the methane that completes heat exchange in the precooler 14 continues to flow to the wall cooling channel of the combustion chamber 15. The low-temperature methane and the high-temperature combustion gas in the combustion chamber 15 complete heat exchange in the wall cooling channel. The clutch 11 is in a closed state, and the gaseous methane then flows to the fuel turbine 10, driving the output shaft of the fuel turbine 10 to drive the fuel pump 13 and the oxidant pump 12 at the same time. At this time, methane flows to the gas generator 16, and the liquid oxygen in the oxidant tank also flows to the gas generator 16 after being pressurized by the oxidant pump 12. Methane and liquid oxygen burn and react in the gas generator 16 to produce high-temperature rich fuel gas that flows to the main turbine, driving the main turbine to drive the compressor to pressurize the incoming air. The rich fuel gas after vortex driving flows to the combustion chamber 15, and burns and reacts with the pressurized air in the combustion chamber 15 to produce high-temperature fuel gas that is discharged through the tail nozzle.

[0043] The second working mode is the stamping mode, such as Figure 2 As shown, the specific working principle is: the incoming air enters the intake duct, and the incoming air is controlled to flow to the combustion chamber 15 by controlling the conversion valve. The low-temperature liquid methane in the fuel tank is pressurized by the fuel pump 13 and flows directly to the wall cooling channel of the combustion chamber 15. The low-temperature methane and the high-temperature combustion gas in the combustion chamber 15 complete heat exchange in the wall cooling channel, and the liquid methane is heated and vaporized. After that, the gaseous methane flows to the fuel turbine 10, driving the output shaft of the fuel turbine 10 to drive the fuel pump 13. At this time, the clutch 11 is in a disengaged state, and the fuel turbine 10 does not drive the oxidant pump 12 to work; methane flows directly to the combustion chamber 15, and the methane fuel and the air pressurized by the intake duct are burned in the combustion chamber 15 to produce high-temperature combustion gas and discharge it through the tail nozzle.

[0044] The present invention adopts a friction clutch 11 to control whether the fuel turbine 10 transmits shaft work to the oxidant pump 12. The friction clutch 11 is mainly composed of four parts: an active disc, a driven disc, a clamping mechanism and an operating mechanism. The active disc is connected to the shaft of the fuel turbine 10, and the driven disc is connected to the shaft of the oxidant pump 12. When working in the turbine mode, the clamping mechanism ensures that the clutch 11 is in an engaged state, so that the fuel turbine 10 drives the oxidant pump 12 to work. When working in the stamping state, the clamping mechanism is separated by the operating mechanism, and a free gap is generated between the active disc and the driven disc. At this time, the shaft of the fuel turbine 10 and the shaft of the oxidant pump 12 are disconnected, the oxidant pump 12 stops working, and only the fuel pump 13 is in working state.

[0045] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. Common turbine fuel supply system with clutch for fuel precooling ATR, characterized in that, include: A fuel turbine (10) configured to rotate under the drive of fuel; A fuel pump (13) is mounted thereon; A clutch (11), whose active disc is mounted on the fuel turbine (10), and whose driven disc is mounted with an oxidant pump (12). The clutch (11) is used to drive the fuel pump (13) and the oxidant pump (12) to rotate under the rotation of the fuel turbine (10) when in a closed state, thereby providing power for the flow of fuel and oxidant.

2. The common turbine fuel supply system with clutch for fuel precooling ATR according to claim 1, characterized in that: Also includes: A precooler (14) having an air flow path inlet, an air flow path outlet, a fuel flow path inlet, and a fuel flow path outlet; Its air flow path inlet is connected to the air intake duct outlet; Its air flow path outlet is connected to the compressor inlet; Its fuel flow path inlet is connected to the outlet of the fuel pump (13); The precooler (14) is used to utilize low-temperature fuel from the fuel pump (13) to cool high-temperature incoming air, so that the incoming air is lowered in temperature and then delivered to the compressor.

3. The common turbine fuel supply system with clutch for fuel precooling ATR according to claim 2, characterized in that: Also includes: A combustion chamber (15) having a gas inlet and an air inlet; Its gas inlet is connected to the gas outlet of the ATR's main turbine; Its air inlet is connected to the outlet of the compressor; The combustion chamber (15) is used for fully burning the rich fuel gas from the main turbine and the air from the compressor.

4. The common turbine fuel supply system with clutch for fuel precooling ATR according to claim 2, characterized in that: The middle part of the fuel pipeline between the precooler (14) and the fuel turbine (10) is arranged close to the combustion chamber (15) and is used to heat the fuel in the fuel pipeline using the heat of the combustion chamber (15), so that the liquid fuel in the fuel pipeline is vaporized into gaseous fuel, which then enters the fuel turbine (10) and drives the fuel turbine (10) to rotate.

5. The common turbine fuel supply system with clutch for fuel precooling ATR according to claim 3, characterized in that: Also includes: A gas generator (16) having a gas inlet, an oxidant inlet, and a gas outlet; Its gas inlet is connected to the gas outlet of the fuel turbine (10); Its gas outlet is connected to the gas inlet of the main turbine; Its oxidant inlet is connected to the outlet of the oxidant pump (12); The gas generator (16) is used to drive the gas fuel of the fuel turbine (10) to pre-react with the oxidant in the gas generator (16), and to deliver the pre-reacted gas to the main turbine of the ATR.

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