Integrated closed circulation system for RBCC engine

Abstract

The invention discloses an integrated closed circulation system for an RBCC engine, and solves the problems that a constant-pressure extrusion mode of an existing RBCC engine propellant supply system is not suitable for variable working condition adjustment of an RBCC rocket thrust chamber, and a high-pressure storage tank is huge in structure, large in weight and not beneficial to application and expansion of the system on the day. According to the system, high-temperature oxygen is generated through catalytic decomposition of hydrogen peroxide and acts on the turbine, then the hydrogen peroxide pump and the coal oil pump are driven to work, integrated pressurization, supply and adjustment of propellants can be carried out on the multiple rocket thrust chambers and the ramjet combustion chamber at the same time, and therefore wide-range fuel oil adjustment is met, and a widely-applied electric pump system can be replaced; and the structural envelope and weight are greatly reduced, so that the power requirement of a longer voyage is met.

Description

Technical Field

[0001] The present invention relates to an apparatus for supplying propellants for an RBCC engine, and more particularly to an integrated closed-loop system for an RBCC engine. Background Art

[0002] A Rocket-Based-Combined-Cycle (RBCC) engine integrates a ramjet engine with a high specific impulse and a rocket engine with a high thrust-to-weight ratio in one flow path, taking into account the advantages of both and being able to operate within a relatively wide Mach number range and altitude. Therefore, the RBCC engine has capabilities such as short-time acceleration and long-range flight, and is expected to become the main power plant for hypersonic aircraft and aerospace transportation systems.

[0003] The RBCC engine includes a propellant supply system, where the propellants include fuel and high-temperature oxygen. Existing RBCC engine propellant supply systems take into account the requirements of the above two types of engines and have characteristics such as high-low pressure compounding, multi-medium management, and wide-range regulation, but have many thermal components and management components, and the system is complex. The special lifting body configuration of a hypersonic aircraft determines that its propellant loading space is limited, while the long-range cruise operation mode of the aircraft requires it to increase the fuel loading. To resolve the contradiction between the two aspects, only by optimizing the RBCC engine propellant supply structure and reducing the engine volume ratio.

[0004] Currently, in the propellant supply systems related to RBCC engines, among the limited several products, most adopt an extrusion-type delivery system, that is, a high-pressure gas cylinder is used to store gas to pressurize the storage tank. When the chamber pressure in the rocket thrust chamber is high and the supply pressure of the ramjet fuel system is large, the gas consumption is large, the volume ratio of the gas cylinder is large, and the structure of the high-pressure storage tank is heavy. These situations seriously affect the miniaturization and lightweight design of the RBCC engine, and are not conducive to increasing the fuel loading and range of the lifting body configuration aircraft.

[0005] Chinese Patent Invention CN112628016A discloses an extrusion-type supply system for an RBCC engine, which integrates the flow paths of nitrogen tetroxide, anhydrous hydrazine, and kerosene into an integrated supply and regulation system. Since the three media need to share a pressurization subsystem based on a high-pressure gas cylinder, the volume of the high-pressure gas cylinder is large, and the propellant storage tanks are all high-pressure storage tanks with thick walls and large weights. Therefore, the volume and structural mass of the high-pressure gas cylinder and the propellant storage tank in the integrated supply and regulation system of this patent invention are large, affecting the compact and lightweight design of the engine.

[0006] Chinese Invention Patent CN111946490A discloses a gas pressurized attitude and orbital control propellant system based on an electric pump, including a gas generator pressurization module based on an electric pump, a high-temperature oxygen storage tank, a fuel storage tank, an orbital control engine, an attitude control engine, and an electric explosion valve. In this technical invention, the gas generator pressurization module based on an electric pump provides high-pressure extrusion gas for the storage tank, but the pressurization pressure cannot be adjusted, and it can only provide a constant medium supply for multiple rocket thrust chambers downstream. In addition, the supply system in this patent saves high-pressure large-volume gas cylinders, but the storage tank is still a high-pressure storage tank. When the volume is large, its structural weight cannot be ignored, which is not conducive to the lightweight design of the system. Summary of the Invention

[0007] The object of the present invention is to solve the problems that the constant-pressure extrusion method of the existing propellant supply system is not applicable to the variable-condition adjustment of the RBCC rocket thrust chamber, and the high-pressure storage tank has a large structure and heavy weight, which is not conducive to the application and expansion of the system in space, and to provide an integrated closed-loop system for the RBCC engine.

[0008] To achieve the above object, the technical solution adopted by the present invention is as follows:

[0009] An integrated closed-loop system for an RBCC engine, including: a hydrogen peroxide supply module for storing hydrogen peroxide under low pressure and a kerosene supply module for storing kerosene under low pressure;

[0010] The hydrogen peroxide supply module is connected to the input end of the hydrogen peroxide pump through a liquid pipeline. The output end of the hydrogen peroxide pump is respectively connected to the input end of the regulating valve and the hydrogen peroxide valves of n rocket thrust chambers through liquid pipelines. The hydrogen peroxide valves of n rocket thrust chambers are respectively connected to the heads of n rocket thrust chambers through liquid pipelines. The output end of the regulating valve is sequentially connected to the gas generator valve and the input end of the gas generator through a liquid pipeline. The output end of the gas generator is connected to the turbine.

[0011] The hydrogen peroxide supply module is connected to the input end of the hydrogen peroxide pump through a liquid pipeline. The output end of the hydrogen peroxide pump is respectively connected to the input end of the regulating valve and the hydrogen peroxide valves of n rocket thrust chambers through n liquid pipelines. The hydrogen peroxide valves of n rocket thrust chambers are respectively connected to the heads of n rocket thrust chambers through liquid pipelines. The output end of the regulating valve is sequentially connected to the gas generator valve and the input end of the gas generator through a liquid pipeline. The output end of the gas generator is connected to the turbine; where n≥1;

[0012] The kerosene supply module is connected to the input end of the kerosene pump through a liquid pipeline. The output end of the kerosene pump is connected to the kerosene valves of n rocket thrust chambers and the positions near the heads of the n rocket thrust chambers through the liquid pipeline in sequence. The output end of the kerosene pump is connected to the ramjet supply module and multiple injectors of the ramjet flow channel through the liquid pipeline in sequence. The kerosene pump is a non-electric pump and can rotate under the action of external force.

[0013] The rotating shafts of the turbine, the hydrogen peroxide pump, and the kerosene pump are integrated rotating shafts. The hydrogen peroxide pump is a non-electric pump and can rotate with the rotating shaft under the action of the turbine to pressurize the hydrogen peroxide storage tank and the kerosene storage tank, so that hydrogen peroxide continuously enters the gas generator for catalytic decomposition and releases energy to obtain high-temperature oxygen. The high-temperature oxygen can make the turbine drive the hydrogen peroxide pump and the kerosene pump to rotate through the rotating shaft, so that hydrogen peroxide and kerosene are pressurized in the hydrogen peroxide pump and the kerosene pump respectively, realizing the cyclic output of hydrogen peroxide, and at the same time making kerosene enter the rocket thrust chamber.

[0014] Further, the hydrogen peroxide supply module includes a hydrogen peroxide storage tank for storing hydrogen peroxide under low pressure and a hydrogen peroxide valve;

[0015] The output end of the hydrogen peroxide storage tank is connected to the input end of the hydrogen peroxide valve through a liquid pipeline, and the output end of the hydrogen peroxide valve is connected to the input end of the hydrogen peroxide pump through a liquid pipeline.

[0016] Further, the kerosene supply module includes a kerosene storage tank for storing kerosene under low pressure and a kerosene valve;

[0017] The output end of the kerosene storage tank is connected to the input end of the kerosene valve through a liquid pipeline, and the output end of the kerosene valve is connected to the input end of the kerosene pump through a liquid pipeline.

[0018] Further, nitrogen is filled in both the hydrogen peroxide storage tank and the kerosene storage tank, and the initial air pressure is 0.05 MPa to 0.35 MPa.

[0019] Further, the ramjet supply module includes a kerosene flow regulating valve and M kerosene valves for injectors at all levels;

[0020] The input end of the kerosene flow regulating valve is connected to the output end of the kerosene pump through a liquid pipeline, and the output end is connected to the input ends of M kerosene valves for injectors at all levels through multiple liquid pipelines. The output ends of the M kerosene valves for injectors at all levels are respectively connected to M injectors of the ramjet flow channel through liquid pipelines, where M≥1.

[0021] Further, a catalytic bed is connected near the input end in the gas generator, and the catalytic bed can catalytically decompose hydrogen peroxide.

[0022] Further, the catalytic bed is a silver mesh.

[0023] The beneficial effects of the present invention are as follows:

[0024] (1) An integrated closed-loop cycle system and control method for an RBCC engine provided by the present invention can first adjust the flow rate of hydrogen peroxide entering the generator to regulate the flow rate of high-temperature oxygen driven by the turbine, change the turbine input work, and then change the turbine speed as well as the flow rate and head of the pump. Finally, it changes the flow rate of the propellant entering the rocket thrust chamber and the ramjet engine, and can achieve continuous variable-condition and multi-modal regulation of the RBCC engine.

[0025] (2) An integrated closed-loop cycle system for an RBCC engine provided by the present invention has a high turbine work transmission efficiency and a small proportion of structural weight. It can adapt to the scale expansion and extended working time of the RBCC engine, and has good adaptability and flexibility.

[0026] (3) An integrated closed-loop cycle system for an RBCC engine provided by the present invention, due to the use of turbocharging, both the hydrogen peroxide storage tank and the kerosene storage tank are low-pressure storage tanks, which can reduce the structural weight of the storage tank, greatly reduce the nitrogen demand, and is conducive to the compactification and miniaturization of the system structure.

[0027] (4) An integrated closed-loop cycle system for an RBCC engine provided by the present invention adopts a turbine closed-loop system. The turbine is discharged into the internal flow channel of the RBCC engine through the rocket thrust chamber, participates in secondary combustion, improves the engine performance, and reduces the problems of the overall assembly of the aircraft caused by the emission of high-temperature oxygen. The system scheme is simple.

[0028] (5) An integrated closed-loop cycle system for an RBCC engine provided by the present invention can integrally pressurize, supply, and regulate the propellant for multiple rocket thrust chambers and ramjet combustors, so as to meet a wide range of fuel regulation. It can replace the widely used electric pump system, and the structural envelope and weight are greatly reduced, thus meeting the power requirements for a longer flight range. Description of the Drawings

[0029] Figure 1 is a schematic structural diagram of an embodiment of an integrated closed-loop cycle system for an RBCC engine provided by the present invention.

[0030] In the figure, 1 - hydrogen peroxide storage tank; 2 - hydrogen peroxide valve; 3 - hydrogen peroxide pump; 4 - kerosene storage tank; 5 - kerosene valve; 6 - kerosene pump; 7 - regulating valve; 8 - gas generator valve; 9 - gas generator; 10 - turbine; 11 - kerosene valves of each stage of injector; 12 - kerosene valve of the rocket thrust chamber; 13 - hydrogen peroxide valve of the rocket thrust chamber; 14 - kerosene flow regulating valve; 15 - rocket thrust chamber. Detailed Embodiments

[0031] To make the objectives, advantages, and features of the present invention clearer, the following further elaborates in detail on an integrated closed-cycle system for an RBCC engine proposed by the present invention in conjunction with the accompanying drawings and specific embodiments. According to the following specific implementation manners, the advantages and features of the present invention will be clearer.

[0032] An integrated closed-cycle system for an RBCC engine in this embodiment, as Figure 1 shown, includes a hydrogen peroxide storage tank 1 for storing hydrogen peroxide at low pressure and a hydrogen peroxide valve 2; the output end of the hydrogen peroxide storage tank 1 is connected to the input end of the hydrogen peroxide valve 2 through a liquid pipeline, the output end of the hydrogen peroxide valve 2 is connected to the input end of a hydrogen peroxide pump 3 through a liquid pipeline, and the output end of the hydrogen peroxide pump 3 is divided into three paths. One path passes through a regulator 7 for flow regulation, and a gas generator valve 8 is opened to enter a gas generator 9 for a catalytic reaction. A catalytic bed composed of a silver mesh is connected near the input end in the gas generator 9; high-temperature oxygen is generated after the catalytic reaction; the high-temperature oxygen enters a turbine 10 to drive the turbine 10 to do work, and the high-temperature oxygen after driving the turbine 10 flows through a pipeline to the head of a rocket thrust chamber 15, and finally participates in secondary combustion heat release in the rocket thrust chamber 15 or is discharged into a ram flow channel, improving the performance of the engine and solving the problem brought by the emission of high-temperature oxygen. The other two paths of the output end of the hydrogen peroxide pump 3 are respectively connected to two rocket thrust chamber hydrogen peroxide valves 13 through two liquid pipelines, and the two rocket thrust chamber hydrogen peroxide valves 13 are respectively connected to the heads of two rocket thrust chambers 15 through liquid pipelines.

[0033] The high-temperature oxygen generated by the single-component catalytic decomposition of hydrogen peroxide through the gas generator 9 is used as the driving energy source for the turbine 10. The high-temperature oxygen after hydrogen peroxide catalysis has the characteristics of high energy density, requires less oxygen consumption for driving the turbine 10, and the designed rotational speed of the turbine 10 is high, which is beneficial to the miniaturized design of the turbine 10 and the pump structure. Compared with the extrusion system and the gas pressurization system, the pump pressure structure adopted in the present invention has a lighter mass, and the miniaturized design makes the system structure volume account for a relatively small proportion, so the fuel loading of the engine can be increased.

[0034] It also includes a kerosene storage tank 4 for storing kerosene under low pressure and a kerosene valve 5; the output end of the kerosene storage tank 4 is connected to the input end of the kerosene valve 5 through a liquid pipeline, the output end of the kerosene valve 5 is connected to the input end of a kerosene pump 6 through a liquid pipeline, and the output end of the kerosene pump 6 is divided into three paths; two of which are respectively connected to two rocket thrust chamber kerosene valves 12 through liquid pipelines, and each rocket thrust chamber kerosene valve 12 is connected to a position near the head of the rocket thrust chamber 15, and the third path is connected to the input end of a kerosene flow regulating valve 14 through a liquid pipeline, and the output end of the kerosene flow regulating valve 14 is connected to the input ends of three stage injector kerosene valves 11 through three liquid pipelines respectively, and the output ends of the three stage injector kerosene valves 11 are respectively connected to three injectors of the ramjet flow path through liquid pipelines.

[0035] The air pressures in the hydrogen peroxide storage tank 1 and the kerosene storage tank 4 can be set to 0.35 MPa ± 0.05 MPa.

[0036] During the supply process of kerosene, the three paths of kerosene output from the output end of the kerosene pump 6, two of which respectively flow into two rocket thrust chambers 15, and the third path supplies the injectors of each stage of the ramjet flow path according to the fuel supply law required by the engine and in proportion. In this process, the continuous variable operating condition adjustment of the RBCC engine can be achieved by changing the propellant flow rates entering the rocket thrust chamber 15 and the ramjet engine.

[0037] During the supply process of high-temperature oxygen and kerosene, the continuous variable operating condition adjustment of the RBCC engine can be achieved by changing the high-temperature oxygen and kerosene flow rates entering the rocket thrust chamber 15 and the ramjet engine. The specific implementation method is that first, the hydrogen peroxide flow rate entering the gas generator 9 is adjusted through a regulating valve 7 to adjust the oxygen flow rate driven by the turbine 10, change the input work of the turbine 10, and then change the rotational speed of the turbine 10 and the flow rate and head of the pump, and finally change the high-temperature oxygen and kerosene flow rates entering the rocket thrust chamber 15 and the ramjet engine, so as to achieve the continuous variable operating condition adjustment of the RBCC engine.

[0038] A silver mesh catalytic bed can be arranged at the head of the rocket thrust chamber 15. Hydrogen peroxide flows into the head of the rocket thrust chamber 15 and is catalytically decomposed by the silver mesh catalytic bed in the rocket thrust chamber 15 to generate high-temperature oxygen. At the same time, kerosene flows into a position near the head of the rocket thrust chamber 15 in the rocket thrust chamber 15. The high-temperature oxygen and kerosene are quickly mixed and burned in the rocket thrust chamber 15 to generate high-temperature and high-pressure oxygen, which is discharged into the ramjet flow path through the rocket nozzle. The high-temperature oxygen and kerosene autoignite after mixing, eliminating the need for forced ignition by an igniter and reducing the complexity of the system.

[0039] For the actual engineering application of an RBCC engine, the fuel supply system should not only meet the thrust adjustment and control requirements of the rocket thrust chamber 15, but also ensure the equivalence ratio adjustment and safety margin control of the ramjet flow path. In this embodiment, the ramjet fuel supply system is integrated with the pump-pressurized circulation system for the propellant supply of the RBCC engine, that is, a set of hydrogen peroxide turbopressurized closed-loop circulation system is adopted to integrally pressurize, supply, and regulate the propellants for multiple rocket thrust chambers 15 and ramjet combustion chambers, so as to meet the wide-range fuel regulation, replace the widely used electric pump system, and greatly reduce the structural envelope and weight, thereby meeting the power requirements for a longer flight range.

[0040] The turbine 10 is serially arranged with the rocket thrust chamber 15, and the high-temperature oxygen after driving the turbine 10 is input into the rocket thrust chamber 15 again to burn and release heat together with the main propellant component in the rocket thrust chamber 15, and further expand and afterburn. This cycle can obtain a higher specific impulse of the engine. The high-temperature oxygen discharge channel of the turbine 10 is integrated on the rocket thrust chamber 15, and the oxygen in the turbine 10 enters the ramjet combustion chamber after participating in the combustion in the rocket thrust chamber 15. Therefore, this cycle system also solves the exhaust problem of the hypersonic engine with a closed aircraft shape.

[0041] A method for using an integrated closed-loop circulation system for an RBCC engine is as follows:

[0042] Open the hydrogen peroxide valve 2, kerosene valve 5, and gas generator valve 8, and close the rocket thrust chamber hydrogen peroxide valve 13 and rocket thrust chamber kerosene valve 12. The hydrogen peroxide in the hydrogen peroxide tank 1 is successively extruded to the hydrogen peroxide valve 2, hydrogen peroxide pump 3, regulating valve 7, gas generator valve 8, and gas generator 9 through the internal pressure difference, and the hydrogen peroxide is catalytically decomposed in the gas generator 9 to generate high-temperature oxygen and input it to the turbine 10 to drive the integrated rotating shaft, hydrogen peroxide pump 3, and kerosene pump 6 to rotate together, forming a work cycle; at the same time, the high-temperature oxygen is input into the head of the rocket thrust chamber 15 through the output end of the turbine 10.

[0043] Adjust the hydrogen peroxide flow rate entering the gas generator 9 through the regulating valve 7 to adjust the oxygen flow rate driven by the turbine 10, and then adjust the working efficiency of the hydrogen peroxide pump 3 and kerosene pump 6 to achieve the effect of controlling the flow rate of the propellant input into the rocket thrust chamber 15.

[0044] The rotating shafts of the hydrogen peroxide pump 3 and the kerosene pump 6 rotate together to respectively increase the negative pressure in the hydrogen peroxide storage tank 1 and the kerosene storage tank 4. Open the hydrogen peroxide valve 13 of the rocket thrust chamber and the kerosene valve 12 of the rocket thrust chamber. The hydrogen peroxide storage tank 1 outputs hydrogen peroxide. After passing through the hydrogen peroxide pump 3, one path sequentially passes through the gas generator valve 8, the gas generator 9, and the turbine 10 to perform a work cycle, and the other path enters the heads of the two rocket thrust chambers 15 through two hydrogen peroxide valves 13 of the rocket thrust chamber.

[0045] The kerosene storage tank 4 outputs kerosene, which sequentially passes through the kerosene pump 6 and two kerosene valves 12 of the rocket thrust chamber and enters the positions near the heads of the two rocket thrust chambers. At the same time, the kerosene flow regulating valve 14 and the kerosene valves 11 of each stage of the injector are opened according to the engine requirements; the kerosene passes through the kerosene flow regulating valve 14 and the kerosene valves 11 of each stage of the injector after passing through the kerosene pump 6 and enters the injector of the ram flow channel for injection.

[0046] When the supply of kerosene and high-temperature oxygen is stopped, the gas generator valve 8, the hydrogen peroxide valve 13 of the rocket thrust chamber, and the kerosene valve 12 of the rocket thrust chamber are closed to complete the control of the pump-pressurized circulation system.

[0047] Through the above method, an integrated closed-cycle system for an RBCC engine of the present invention can realize the continuous variable working condition adjustment of the RBCC engine, and the integrated design of the supply system reduces the volume and structural mass of the system.

[0048] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. An integrated closed cycle system for an RBCC engine, characterized in that, Comprising: A hydrogen peroxide supply module for storing hydrogen peroxide under low pressure and a kerosene supply module for storing kerosene under low pressure; The hydrogen peroxide supply module is connected to the input end of a hydrogen peroxide pump (3) through a liquid pipeline. The output end of the hydrogen peroxide pump (3) is respectively connected to the input end of a regulating valve (7) and n hydrogen peroxide valves (13) of rocket thrust chambers through liquid pipelines. The n hydrogen peroxide valves (13) of rocket thrust chambers are respectively connected to the heads of the n rocket thrust chambers through liquid pipelines. The output end of the regulating valve (7) is successively connected to a gas generator valve (8) and a gas generator (9) through a liquid pipeline. The output end of the gas generator (9) is connected to a turbine (10), where n≥1; The kerosene supply module is connected to the input end of a kerosene pump (6) through a liquid pipeline. The output end of the kerosene pump (6) is successively connected to n kerosene valves (12) of rocket thrust chambers and the n rocket thrust chambers through liquid pipelines. The output end of the kerosene pump (6) is simultaneously connected to a ramjet supply module and multiple injectors of a ramjet flow channel through liquid pipelines; The turbine (10) and the rotating shafts of the hydrogen peroxide pump (3) and the kerosene pump (6) are integrated rotating shafts.

2. The integrated closed cycle system for an RBCC engine according to claim 1, wherein: The hydrogen peroxide supply module includes a hydrogen peroxide storage tank (1) for storing hydrogen peroxide under low pressure and a hydrogen peroxide valve (2); The output end of the hydrogen peroxide storage tank (1) is connected to the input end of the hydrogen peroxide valve (2) through a liquid pipeline. The output end of the hydrogen peroxide valve (2) is connected to the input end of the hydrogen peroxide pump (3) through a liquid pipeline.

3. The integrated closed cycle system for an RBCC engine according to claim 2, wherein: The kerosene supply module includes a kerosene storage tank (4) for storing kerosene under low pressure and a kerosene valve (5); The output end of the kerosene storage tank (4) is connected to the input end of the kerosene valve (5) through a liquid pipeline. The output end of the kerosene valve (5) is connected to the input end of the kerosene pump (6) through a liquid pipeline.

4. The integrated closed cycle system for an RBCC engine according to claim 3, characterized in that: Both the hydrogen peroxide storage tank (1) and the kerosene storage tank (4) are filled with nitrogen, maintaining the air pressure at 0.05 MPa to 0.35 MPa.

5. The integrated closed cycle system for an RBCC engine according to claim 1, characterized in that: The ramjet supply module includes a kerosene flow regulating valve (14) and M kerosene valves (11) for injectors at all levels; The input end of the kerosene flow regulating valve (14) is connected to the output end of the kerosene pump (6) through a liquid pipeline. The output end is respectively connected to the input ends of the M kerosene valves (11) for injectors at all levels through multiple liquid pipelines. The output ends of the M kerosene valves (11) for injectors at all levels are respectively connected to the M injectors of the ramjet flow channel through liquid pipelines, where M≥1.

6. The integrated closed cycle system for an RBCC engine according to claim 1, characterized in that: A catalytic bed is connected near the input end inside the gas generator (9).

7. An integrated closed cycle system for an RBCC engine according to claim 6, characterized in that: The catalytic bed is a silver mesh.

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