Combined engine and control method thereof

Abstract

The invention discloses a combined engine and a control method thereof. The combined engine comprises a control assembly, an air inlet channel, a turbine core machine, a nuclear reactor system, a propellant supply system and a spray pipe assembly, the control assembly is used for controlling the air inlet end of the nuclear reactor system to be selectively connected with one of the air inlet channel, the turbine core machine or the propellant supply system through a pipeline; the gas outlet end of the nuclear reactor system is connected with the spray pipe assembly. The air inlet end of the nuclear reactor system is controlled by the control assembly to be connected with the air inlet channel, the turbine core machine and the propellant supply system through pipelines so that the combined engine can enter a nuclear stamping mode, a nuclear turbine mode and a non-air-suction mode. The ultra-high-speed aircraft has the characteristics that the fuel economy is high, the ultra-high-speed aircraft can work in a non-atmospheric environment, flight in different speed domains can be realized by adopting different engine modes, and the requirement of the ultra-high-speed aircraft for aerospace transportation can be met.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and particularly to a combined engine and its control method. Background Art

[0002] The main function of an aircraft engine is to provide propulsion power or supporting force for the aircraft, and it is the core component of the aircraft. Existing aircraft engines can be divided into various categories such as turbojet engines, ramjet engines, and non-air-breathing engines, and each type of engine has its own operating speed range.

[0003] In order to achieve wide-speed-range flight of the engine, in the prior art, different engines are combined to form a combined engine. A combined engine is an engine composed of two or more engines with different operating modes, and has a wider operating speed range. In recent years, the related technologies of combined engines have developed rapidly. From the early non-air-breathing and ramjet combined cycle engines and turbine-based ramjet combined cycle engines to the current air-turbine ramjet combined engines, etc., they have all provided new optional power systems for hypersonic aircraft, etc.

[0004] However, the non-air-breathing and ramjet combined cycle engine uses the jet injection effect of the non-air-breathing engine to make up for the insufficient ram compression ability in the low-speed section. The process of accelerating the engine to the Mach number at which it operates in the ram mode consumes too much propellant, and the fuel economy is not high; the turbine-based ramjet combined cycle engine is difficult to design in a coordinated manner and cannot operate in an environment without atmosphere; the flight speed upper limit of the air-turbine ramjet combined engine cannot meet the requirements of hypersonic aircraft for space transportation. Summary of the Invention

[0005] Based on this, in view of the above technical problems, it is necessary to provide a combined engine and its control method, which has high fuel economy, can operate in an airless environment, and can achieve different-speed-range flight by using different engine modes, and can meet the requirements of hypersonic aircraft for space transportation.

[0006] In a first aspect, the present invention provides a combined engine, including a control component, and an air inlet duct, a turbine core engine, a nuclear reactor system, a propellant supply system, and a nozzle assembly connected by pipelines;

[0007] The control component is used to control the intake end of the nuclear reactor system to selectively connect with the air inlet duct, the turbine core engine, or the propellant supply system through a pipeline;

[0008] The outlet end of the nuclear reactor system is connected to the nozzle assembly.

[0009] In one embodiment, the turbine core engine is provided with a first transmission shaft, a second transmission shaft, a fan, a compressor, a high-pressure turbine and a low-pressure turbine;

[0010] The fan is connected to the low-pressure turbine through the first transmission shaft, the compressor and the high-pressure turbine are connected through the second transmission shaft, and the first transmission shaft and the second transmission shaft are coaxial;

[0011] The intake end of the fan is connected to the outlet end of the intake duct, the intake end of the compressor is connected to the outlet end of the fan, and the outlet end of the high-pressure turbine is connected to the intake end of the low-pressure turbine.

[0012] In one embodiment, the propellant supply system includes a working fluid storage tank, a working fluid pump and a working fluid turbine. The inlet end of the working fluid pump is connected to the outlet end of the working fluid storage tank, and the working fluid turbine is connected to the working fluid pump through a third transmission shaft.

[0013] In one embodiment, the nuclear reactor system includes a low-temperature nuclear reactor and a high-temperature nuclear reactor. The high-temperature nuclear reactor is cylindrical and sleeved outside the low-temperature nuclear reactor.

[0014] In one embodiment, the pipeline control assembly includes a first control valve, a second control valve, a third control valve, a fourth control valve, a fifth control valve and a control module for controlling the working conditions of each control valve;

[0015] The nozzle assembly includes a variable geometry nozzle and a regenerative cooling nozzle.

[0016] In one embodiment, the outlet end of the intake duct, the outlet end of the compressor, and the outlet end of the working fluid pump are all connected to the intake end of the first control valve, and the intake end of the low-temperature nuclear reactor is connected to the outlet end of the first control valve;

[0017] The outlet end of the low-temperature nuclear reactor is connected to the intake end of the second control valve, and the intake end of the high-pressure turbine is connected to the outlet end of the second control valve;

[0018] The outlet end of the second control valve and the outlet end of the low-pressure turbine are both connected to the intake end of the third control valve;

[0019] The outlet end of the third control valve is connected to the intake end of the high-temperature nuclear reactor, and the outlet end of the high-temperature nuclear reactor is connected to the intake end of the fifth control valve;

[0020] The nozzle inlets of the variable geometry nozzle and the regenerative cooling nozzle are both connected to the outlet end of the fifth control valve;

[0021] The outlet end of the working fluid turbine is connected to the intake end of the fourth control valve, and the outlet end of the fourth control valve is connected to the intake end of the high-temperature nuclear reactor;

[0022] The inlet of the cooling channel of the regenerative cooling nozzle is connected to the outlet end of the working fluid pump, and the outlet of the cooling channel of the regenerative cooling nozzle is connected to the inlet end of the working fluid turbine.

[0023] In a second aspect, the present invention further provides a combined engine control method for controlling the above-mentioned combined engine to enter different operating modes. By controlling the control component, the inlet end of the nuclear reactor system is connected to the air inlet duct through a pipeline, and the combined engine enters the nuclear ramjet mode;

[0024] By controlling the control component, the inlet end of the nuclear reactor system is connected to the turbine core engine through a pipeline, and the combined engine enters the nuclear turbine mode;

[0025] By controlling the control component, the inlet end of the nuclear reactor system is connected to the propellant supply system through a pipeline, and the combined engine enters the non-air-breathing mode.

[0026] In one embodiment, by controlling the control module, the first control valve connects the outlet end of the air inlet duct to the inlet end of the low-temperature nuclear reactor, the second control valve connects the outlet end of the low-temperature nuclear reactor to the inlet end of the third control valve, the third control valve connects the outlet end of the third control valve to the inlet end of the high-temperature nuclear reactor, the fourth control valve is closed, and the fifth control valve connects the outlet end of the high-temperature nuclear reactor to the nozzle inlet of the variable geometry nozzle, and the combined engine enters the nuclear ramjet mode;

[0027] By controlling the control module, the first control valve connects the outlet end of the compressor to the inlet end of the low-temperature nuclear reactor, the second control valve connects the outlet end of the low-temperature nuclear reactor to the inlet end of the high-pressure turbine, the third control valve connects the outlet end of the low-pressure turbine to the inlet end of the high-temperature nuclear reactor, the fourth control valve is closed, and the fifth control valve connects the outlet end of the high-temperature nuclear reactor to the nozzle inlet of the variable geometry nozzle, and the combined engine enters the nuclear turbine mode;

[0028] By controlling the control module, the first control valve connects the outlet end of the working fluid turbine to the inlet end of the low-temperature nuclear reactor, the second control valve connects the outlet end of the low-temperature nuclear reactor to the inlet end of the third control valve, the third control valve connects the outlet end of the third control valve to the inlet end of the high-temperature nuclear reactor, the fourth control valve is opened, and the fifth control valve connects the outlet end of the high-temperature nuclear reactor to the nozzle inlet of the regenerative cooling nozzle, and the combined engine enters the non-air-breathing mode.

[0029] The beneficial effects of the present invention are:

[0030] (1) In the present invention, the connection relationship of the pipeline is controlled by a control component to realize the alternative selective connection between the air inlet end of the nuclear reactor system and the air inlet duct, the turbine core engine or the propellant supply system, and further realize the free switching among three engine modes of ramjet, turbine and non-air-breathing modes, so that the engine can work in the medium and high speed sections, the low speed section and the airless environment, and can meet the requirements of hypersonic aircraft for space transportation.

[0031] (2) When the combined engine of the present invention is in the nuclear turbine mode and the nuclear ramjet mode, the propulsive working medium is the oncoming gas. The combined engine itself only consumes nuclear fuel for maintaining the operation of the nuclear reactor, and the change in the consumed mass of the engine is small, having excellent specific impulse performance and being able to extend the flight time of the aircraft in the atmosphere; and in the turbine mode and the ramjet mode, the self-carried working medium is not consumed, making the combined engine have high fuel economy; in addition, the energy for heating the gas in each mode comes from the nuclear fission process of the nuclear reactor, so oxygen does not have to be included in the oncoming gas, and thus the aircraft including the combined engine of the present invention can achieve flight to extraterrestrial planets. Description of the Drawings

[0032] Figure 1 is a schematic structural diagram of the combined engine provided by an embodiment of the present invention;

[0033] Figure 2 is a schematic diagram of the ramjet mode of the combined engine provided by an embodiment of the present invention;

[0034] Figure 3 is a schematic diagram of the turbine mode of the combined engine provided by an embodiment of the present invention;

[0035] Figure 4 is a schematic diagram of the non-air-breathing mode of the combined engine provided by an embodiment of the present invention.

[0036] Description of the reference numerals: 100, air inlet duct; 200, first transmission shaft; 210, second transmission shaft; 220, fan; 230, compressor; 240, high-pressure turbine; 250, low-pressure turbine; 300, working medium storage tank; 310, working medium pump; 320, working medium turbine; 330, third transmission shaft; 400, low-temperature nuclear reactor; 410, high-temperature nuclear reactor; 600, first control valve; 610, second control valve; 620, third control valve; 630, fourth control valve; 640, fifth control valve; 700, variable geometry nozzle; 710, regenerative cooling nozzle. Detailed Embodiments

[0037] To make the above objects, features and advantages of the present invention more obvious and understandable, the following detailed description of the specific embodiments of the present invention will be given with reference to the drawings.

[0038] It should be noted that in the description of the present invention, "upper", "lower", "top", "bottom", the orientation or positional relationship is based on the attachment Figure 1 The orientation or positional relationship shown. It should be understood that these orientation terms 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 orientation, be constructed and operated in a specific orientation, and therefore cannot be construed as a limitation on the present invention.

[0039] In one embodiment, as Figure 1 shown, the combined engine of this embodiment includes a control assembly and an air inlet 100, a turbine core engine, a nuclear reactor system, a propellant supply system, and a nozzle assembly connected by pipelines.

[0040] It should be noted that in this embodiment, the turbine core engine, the nuclear reactor system, and the propellant supply system are located inside the engine installation housing, the air inlet 100 is located at the front end of the housing, and the nozzle assembly is located at the rear end of the housing.

[0041] The control assembly is used to control the intake end of the nuclear reactor system to be selectively connected to the air inlet 100, the turbine core engine, or the propellant supply system through a pipeline; the outlet end of the nuclear reactor system is connected to the nozzle assembly.

[0042] Specifically, when the nuclear reactor system is directly connected to the air inlet 100, the combined engine is in nuclear ramjet mode. When the nuclear reactor system is connected to the turbine core engine, the combined engine is in turbine mode. When the reactor system is connected to the propellant supply system, the combined engine is in non-air-breathing mode, that is, rocket mode, and the propellant combustion is used to provide propulsion power in a non-air-breathing state.

[0043] The combined engine of this embodiment can realize the switching of three engine modes: ramjet, turbine, and non-air-breathing modes, enabling the engine to operate in the medium and high speed sections, low speed sections, and non-atmospheric environment, and meeting the needs of aerospace transportation of aircraft.

[0044] In addition, for the incoming air of the air inlet 100 and the turbine core engine, and the incoming working medium of the propellant supply system, after being heated by the nuclear reactor system and discharged from the nozzle assembly, the heating energy comes from the nuclear fission process of the reactor. Then, the incoming gas does not have to contain oxygen and the engine mass change is small. Furthermore, the aircraft including the combined engine of the present invention can achieve flight to extraterrestrial planets and has better specific impulse performance.

[0045] In one of the embodiments, the turbine core engine is provided with a first transmission shaft 200, a second transmission shaft 210, a fan 220, a compressor 230, a high-pressure turbine 240, and a low-pressure turbine 250.

[0046] The fan 220 and the low-pressure turbine 250 are connected by a first transmission shaft 200, the compressor 230 and the high-pressure turbine 240 are connected by a second transmission shaft 210, and the first transmission shaft 200 and the second transmission shaft 210 are coaxial; the air inlet end of the fan 220 is connected to the air outlet end of the air inlet duct 100, the air inlet end of the compressor 230 is connected to the air outlet end of the fan 220, and the air outlet end of the high-pressure turbine 240 is connected to the air inlet end of the low-pressure turbine 250.

[0047] Specifically, the fan 220 is used to perform the first-stage compression on the oncoming air of the air inlet duct 100, and then direct the compressed air to the compressor 230 for further compression. The high-pressure turbine 240 can receive the gas heated by the low-temperature nuclear reactor 400 and is driven by the gas to do work. When the high-pressure turbine 240 rotates, it drives the compressor 230 to provide power under the drive of the second transmission shaft 210. The high-temperature air delivered by the high-pressure turbine 240 to the low-pressure turbine 250 drives the low-pressure turbine 250 to do work, and then the low-pressure turbine 250 provides power for the fan 220.

[0048] In one embodiment, the propellant supply system includes a working fluid storage tank 300, a working fluid pump 310, and a working fluid turbine 320. The inlet end of the working fluid pump 310 is connected to the outlet end of the working fluid storage tank 300, and the working fluid turbine 320 is connected to the working fluid pump 310 through a third transmission shaft 330.

[0049] Specifically, the working fluid storage tank 300 can store working fluids such as liquid hydrogen, liquid methane, or liquid carbon dioxide. The working fluid pump 310 is used to pressurize the working fluid. Driven by the third rotating shaft, the working fluid turbine 320 is used to provide power for the working fluid pump 310.

[0050] In order to meet the upper limit of the allowable temperature of the turbine, in this embodiment, the nuclear reactor system includes a low-temperature nuclear reactor 400 and a high-temperature nuclear reactor 410, which are used to heat the oncoming gas or working fluid in two stages. Among them, the high-temperature nuclear reactor 410 is cylindrical and sleeved outside the low-temperature nuclear reactor 400, and is used to further heat the oncoming gas or working fluid heated by the low-temperature nuclear reactor 400.

[0051] In one embodiment, the pipeline control assembly includes a first control valve 600, a second control valve 610, a third control valve 620, a fourth control valve 630, a fifth control valve 640, and a control module for controlling the working conditions of each control valve; the nozzle assembly includes a variable geometry nozzle 700 and a regenerative cooling nozzle 710.

[0052] In this embodiment, the control module can control the working conditions of each control valve, and then realize different connection relationships of the pipelines connected to the control valves, so as to realize the switching of different modes of the engine.

[0053] In one embodiment, the outlet end of the intake passage 100, the outlet end of the compressor 230, and the working fluid outlet end of the working fluid pump 310 are all connected to the intake end of the first control valve 600, and the intake end of the low-temperature nuclear reactor 400 is connected to the outlet end of the first control valve 600;

[0054] The outlet end of the low-temperature nuclear reactor 400 is connected to the intake end of the second control valve 610, and the intake end of the high-pressure turbine 240 is connected to the outlet end of the second control valve 610;

[0055] The outlet end of the second control valve 610 and the outlet end of the low-pressure turbine 250 are both connected to the intake end of the third control valve 620;

[0056] The outlet end of the third control valve 620 is connected to the intake end of the high-temperature nuclear reactor 410, and the outlet end of the high-temperature nuclear reactor 410 is connected to the intake end of the fifth control valve 640;

[0057] The nozzle inlets of the variable geometry nozzle 700 and the regenerative cooling nozzle 710 are both connected to the outlet end of the fifth control valve 640;

[0058] The outlet end of the working fluid turbine 320 is connected to the intake end of the fourth control valve 630, and the outlet end of the fourth control valve 630 is connected to the intake end of the high-temperature nuclear reactor 410;

[0059] The cooling channel inlet of the regenerative cooling nozzle 710 is connected to the working fluid outlet end of the working fluid pump 310, and the cooling channel outlet of the regenerative cooling nozzle 710 is connected to the intake end of the working fluid turbine 320.

[0060] In this embodiment, the intake end, the outlet end, the working fluid inlet end, and the working fluid outlet end are connected by pipelines or directly connected between components. It should be noted that each control valve can control the connectivity between the ports connected thereto, and thus can switch between different modes of the combined engine.

[0061] Based on the same inventive concept, the present invention also provides a combined engine control method for controlling the combined engine in any of the above embodiments to enter different operating modes. Specifically, the method is as follows:

[0062] By controlling the control component, the intake end of the nuclear reactor system is connected to the intake passage 100 through a pipeline, and the combined engine enters the nuclear ramjet mode; by controlling the control component, the intake end of the nuclear reactor system is connected to the turbine core engine through a pipeline, and the combined engine enters the nuclear turbine mode; by controlling the control component, the intake end of the nuclear reactor system is connected to the propellant supply system through a pipeline, and the combined engine enters the non-air-breathing mode.

[0063] The method of the present invention can switch the modes of the combined engine according to different speed range requirements to adapt to different flight conditions, and can work in the medium and high speed sections, low speed sections, and non-atmospheric environments, meeting the requirements of aerospace transport aircraft.

[0064] In one embodiment, the control module controls the first control valve 600 to connect the outlet end of the intake duct 100 to the intake end of the cryogenic nuclear reactor 400, the second control valve 610 to connect the outlet end of the cryogenic nuclear reactor 400 to the intake end of the third control valve 620, the third control valve 620 to connect the outlet end of the third control valve 620 to the intake end of the high-temperature nuclear reactor 410, the fourth control valve 630 to be closed, and the fifth control valve 640 to connect the outlet end of the high-temperature nuclear reactor 410 to the nozzle inlet of the variable geometry nozzle 700, and the combined engine enters the ramjet mode.

[0065] Specifically, as Figure 2 shown, in the ramjet mode, the oncoming gas first enters the intake duct 100 for compression. At this time, the turbine core engine system is closed, and the oncoming gas sequentially passes through the cryogenic nuclear reactor 400 and the high-temperature nuclear reactor 410 for heating, and then is directly ejected through the variable geometry nozzle 700 to generate thrust.

[0066] The control module controls the first control valve 600 to connect the outlet end of the compressor 230 to the intake end of the cryogenic nuclear reactor 400, the second control valve 610 to connect the outlet end of the cryogenic nuclear reactor 400 to the intake end of the high-pressure turbine 240, the third control valve 620 to connect the outlet end of the low-pressure turbine 250 to the intake end of the high-temperature nuclear reactor 410, the fourth control valve 630 to be closed, and the fifth control valve 640 to connect the outlet end of the high-temperature nuclear reactor 410 to the nozzle inlet of the variable geometry nozzle 700, and the combined engine enters the turbine mode.

[0067] Specifically, as Figure 3 shown, in the turbine mode, the oncoming gas first enters the fan 220 through the intake duct 100. The fan 220 performs the first-stage compression on the oncoming gas, and then guides the compressed gas to the compressor 230 for further compression; the compressor 230 guides the compressed gas into the cryogenic nuclear reactor 400 to increase the temperature, and then the high-pressure turbine 240 receives the gas heated by the cryogenic nuclear reactor 400 and is pushed by it to do work, and provides power for the compressor 230 through the second transmission shaft 210; the high-pressure turbine 240 guides the high-temperature gas heated by the cryogenic nuclear reactor 400 into the low-pressure turbine 250, and the high-temperature gas pushes the low-pressure turbine 250 to do work. The low-pressure turbine 250 provides power for the fan 220 through the first transmission shaft 200; finally, the air is ejected through the variable geometry nozzle 700 to generate thrust.

[0068] The control module controls the first control valve 600 to connect the outlet end of the working fluid turbine 320 and the inlet end of the low-temperature nuclear reactor 400, the second control valve 610 to connect the outlet end of the low-temperature nuclear reactor 400 and the inlet end of the third control valve 620, the third control valve 620 to connect the outlet end of the third control valve 620 and the inlet end of the high-temperature nuclear reactor 410, the fourth control valve 630 is opened, and the fifth control valve 640 is connected to the outlet end of the high-temperature nuclear reactor 410 and the nozzle inlet of the regeneration cooling nozzle 710, and the combined engine enters the non-air-intake mode.

[0069] It should be noted that the cooling channel of the regenerative cooling nozzle 710 is activated only when the fourth control valve 630 is activated.

[0070] Specifically, Figure 4 As shown, in the non-inhalation mode, the air inlet 100 and the turbine core engine are both in a closed state, and the combined engine uses the propulsion working fluid in the working fluid storage box 300 to work. The working fluid is extracted from the working fluid storage box 300 by the working fluid pump 310 and pressurized, and then the working fluid is divided into two streams. The first stream of working fluid first passes through the regenerative cooling nozzle 710 to cool the nozzle, and at the same time, it becomes gaseous. The gaseous working fluid then enters the working fluid turbine 320 to drive it to do work, and the second stream of working fluid directly flows through the low-temperature nuclear reactor 400 to be heated to form a gaseous working fluid. Then, the first stream of gaseous working fluid and the second stream of gaseous working fluid are mixed and flow through the high-temperature nuclear reactor 410 together for further heating, and then introduced into the regenerative cooling nozzle 710 to be ejected to generate thrust.

[0071] It should be noted that in a vacuum environment, it is more difficult for the nozzle to dissipate heat. When the nozzle temperature is too high, the nozzle may melt or the structure may be damaged. The nozzle in this embodiment adopts a regenerative cooling nozzle, and uses a liquid working fluid to cool the regenerative cooling nozzle to avoid damage to the nozzle. In addition, in the non-air-intake mode, the cooling channel of the regenerative cooling nozzle cannot fully accommodate all the propulsion working fluids, and the propulsion working fluid needs to be diverted into two streams, with one stream entering the regenerative cooling channel. Since the liquid working fluid passing through the cooling channel is changed to a gaseous state, the present invention allows the other stream of working fluid to be heated to a gaseous state by a low-temperature nuclear reactor first to avoid the complex situation of gas-liquid mixing when the two streams of working fluids are mixed.

[0072] The above-mentioned embodiments only express several implementation methods of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the present invention. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the attached claims.

Claims

1. A combined engine, characterized in that: It includes a control component and an air inlet (100), a turbine core, a nuclear reactor system, a propellant supply system and a nozzle component connected by pipelines; The control component is used to control the air inlet end of the nuclear reactor system to be selectively connected to an air inlet duct (100), a turbine core engine or a propellant supply system through a pipeline; The gas outlet end of the nuclear reactor system is connected to the nozzle assembly.

2. The combined engine according to claim 1, characterized in that: The turbine core engine is provided with a first transmission shaft (200), a second transmission shaft (210), a fan (220), a compressor (230), a high-pressure turbine (240) and a low-pressure turbine (250); The fan (220) is connected to the low-pressure turbine (250) via a first transmission shaft (200), the compressor (230) is connected to the high-pressure turbine (240) via a second transmission shaft (210), and the first transmission shaft (200) and the second transmission shaft (210) are coaxial; The air inlet end of the fan (220) is connected to the air outlet end of the air inlet duct (100), the air inlet end of the compressor (230) is connected to the air outlet end of the fan (220), and the air outlet end of the high-pressure turbine (240) is connected to the air inlet end of the low-pressure turbine (250).

3. The combined engine according to claim 2, characterized in that: The propellant supply system comprises a working fluid storage box (300), a working fluid pump (310) and a working fluid turbine (320); the working fluid inlet end of the working fluid pump (310) is connected to the working fluid outlet end of the working fluid storage box (300); and the working fluid turbine (320) is connected to the working fluid pump (310) via a third transmission shaft (330).

4. The combined engine according to claim 3, characterized in that: The nuclear reactor system comprises a low-temperature nuclear reactor (400) and a high-temperature nuclear reactor (410); the high-temperature nuclear reactor (410) is cylindrical and sleeved on the outside of the low-temperature nuclear reactor (400).

5. The combined engine according to claim 4, characterized in that: The pipeline control assembly comprises a first control valve (600), a second control valve (610), a third control valve (620), a fourth control valve (630), a fifth control valve (640) and a control module for controlling the working conditions of each control valve; The nozzle assembly includes a variable geometry nozzle (700) and a regenerative cooling nozzle (710).

6. The combined engine according to claim 5, characterized in that: The air outlet end of the air inlet duct (100), the air outlet end of the air compressor (230) and the outlet end of the working fluid pump (310) are all connected to the air inlet end of the first control valve (600), and the air inlet end of the low-temperature nuclear reactor (400) is connected to the air outlet end of the first control valve (600); The gas outlet end of the low-temperature nuclear reactor (400) is connected to the gas inlet end of the second control valve (610), and the gas inlet end of the high-pressure turbine (240) is connected to the gas outlet end of the second control valve (610); The air outlet end of the second control valve (610) and the air outlet end of the low-pressure turbine (250) are both connected to the air inlet end of the third control valve (620); The gas outlet end of the third control valve (620) is connected to the gas inlet end of the high temperature nuclear reactor (410), and the gas outlet end of the high temperature nuclear reactor (410) is connected to the gas inlet end of the fifth control valve (640); The nozzle inlets of the variable geometry nozzle (700) and the regenerative cooling nozzle (710) are both connected to the gas outlet end of the fifth control valve (640); The gas outlet end of the working fluid turbine (320) is connected to the gas inlet end of the fourth control valve (630), and the gas outlet end of the fourth control valve (630) is connected to the gas inlet end of the high temperature nuclear reactor (410); The cooling channel inlet of the regenerative cooling nozzle (710) is connected to the outlet end of the working fluid pump (310), and the cooling channel outlet of the regenerative cooling nozzle (710) is connected to the air inlet end of the working fluid turbine (320).

7. A combined engine control method, used to control the combined engine according to any one of claims 1 to 6 to enter different working modes, characterized in that: The control component controls the air inlet end of the nuclear reactor system to be connected to the air inlet duct (100) through a pipeline, and the combined engine enters a nuclear ramjet mode; The control component controls the air inlet end of the nuclear reactor system to be connected to the turbine core engine through a pipeline, and the combined engine enters the nuclear turbine mode; The control component controls the air intake end of the nuclear reactor system to be connected to the propellant supply system through a pipeline, and the combined engine enters a non-air-breathing mode.

8. The combined engine control method according to claim 7, characterized in that: The control module controls the first control valve (600) to connect the outlet end of the air inlet duct (100) with the air inlet end of the low-temperature nuclear reactor (400), the second control valve (610) to connect the outlet end of the low-temperature nuclear reactor (400) with the air inlet end of the third control valve (620), the third control valve (620) to connect the outlet end of the third control valve (620) with the air inlet end of the high-temperature nuclear reactor (410), the fourth control valve (630) to close, and the fifth control valve (640) to connect the outlet end of the high-temperature nuclear reactor (410) with the nozzle inlet of the variable geometry nozzle (700), so that the combined engine enters a nuclear ramjet mode; The control module controls the first control valve (600) to connect the air outlet of the compressor (230) and the air inlet of the low-temperature nuclear reactor (400), the second control valve (610) to connect the air outlet of the low-temperature nuclear reactor (400) and the air inlet of the high-pressure turbine (240), the third control valve (620) to connect the air outlet of the low-pressure turbine (250) and the air inlet of the high-temperature nuclear reactor (410), the fourth control valve (630) to close, and the fifth control valve (640) to connect the air outlet of the high-temperature nuclear reactor (410) and the nozzle inlet of the variable geometry nozzle (700), so that the combined engine enters the nuclear turbine mode; The control module controls the first control valve (600) to connect the outlet of the working fluid turbine (320) and the inlet of the low-temperature nuclear reactor (400), the second control valve (610) to connect the outlet of the low-temperature nuclear reactor (400) and the inlet of the third control valve (620), the third control valve (620) to connect the outlet of the third control valve (620) and the inlet of the high-temperature nuclear reactor (410), the fourth control valve (630) to open, and the fifth control valve (640) to connect the outlet of the high-temperature nuclear reactor (410) and the nozzle inlet of the regenerative cooling nozzle (710), and the combined engine enters a non-air-intake mode.

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