Combination engine and method of controlling the same

Abstract

The application discloses a combined engine and a control method thereof. The combined engine comprises a control assembly, an air inlet channel, a turbine core engine, a nuclear reactor system, a propellant supply system and a nozzle assembly which are connected through pipelines. The control assembly is used for controlling the air inlet end of the nuclear reactor system to be selectively connected with the air inlet channel, the turbine core engine or the propellant supply system through the pipelines. The air outlet end of the nuclear reactor system is connected with the nozzle assembly. The air inlet end of the nuclear reactor system is connected with the air inlet channel, the turbine core engine and the propellant supply system through the pipelines respectively by the control assembly, so that the combined engine enters the nuclear ram mode, the nuclear turbine mode and the non-suction mode respectively. The combined engine has the characteristics of high fuel economy, working in the atmosphere-free environment, realizing different speed domain flights by using different engine modes and meeting the needs of space transportation of the super-speed aircraft.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine technology, and in particular to a combined engine and its control method. Background Technology

[0002] The primary function of an aircraft engine is to provide propulsion or support for the aircraft, making it a core component. Existing aircraft engines can be categorized into several types, including turbine engines, ramjet engines, and non-air-breathing engines, each with its own operating speed range.

[0003] To achieve wide-speed-range flight, existing technologies combine different engines to form combined engines. Combined engines are composed of two or more engines operating in different modes, resulting in a wider operating speed range. In recent years, combined engine technology has developed rapidly, from early non-air-breathing and ramjet combined cycle engines and turbine-based ramjet combined cycle engines to current air-turbo-ramjet combined engines, all providing new and alternative power systems for hypersonic aircraft.

[0004] However, the non-breathing and ramjet combined cycle engine uses the jet ejection effect of the non-breathing engine to compensate for the insufficient ramjet compression capacity in the low-speed range. The process of accelerating the engine to the Mach number of the ramjet mode consumes too much propellant and has poor fuel economy. The turbine-based ramjet combined cycle engine is difficult to coordinate in design and cannot operate in an environment without an atmosphere. The upper limit of the flight speed of the air turbine-ramjet combined engine cannot meet the requirements of hypersonic aircraft for aerospace transportation. Summary of the Invention

[0005] Based on this, it is necessary to provide a combined engine and its control method to address the above-mentioned technical problems. This engine has high fuel economy, can operate in atmospheric environments, and can achieve flight in different speed ranges using different engine modes, thus meeting the needs of hypersonic aircraft for aerospace transportation.

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

[0007] The control components are used to control the air intake of the nuclear reactor system to be selectively connected to the air intake, turbine core, or propellant supply system via pipelines.

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

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

[0010] The fan and the low-pressure turbine are connected via a first drive shaft, and the compressor and the high-pressure turbine are connected via a second drive shaft. The first and second drive shafts are coaxial.

[0011] The fan's inlet is connected to the inlet of the air intake, the compressor's inlet is connected to the fan's outlet, and the high-pressure turbine's outlet is connected to the low-pressure turbine's inlet.

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

[0013] In one embodiment, the nuclear reactor system includes a cryogenic nuclear reactor and a high-temperature nuclear reactor, wherein the high-temperature nuclear reactor is cylindrical and fitted outside the cryogenic 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 operating 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 of the air inlet, the outlet of the compressor, and the outlet of the working fluid pump are all connected to the inlet of the first control valve, and the inlet of the cryogenic nuclear reactor is connected to the outlet of the first control valve.

[0017] The outlet of the cryogenic nuclear reactor is connected to the inlet of the second control valve, and the inlet of the high-pressure turbine is connected to the outlet of the second control valve.

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

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

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

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

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

[0023] Secondly, the present invention also provides a combined engine control method for controlling the above-mentioned combined engine to enter different working modes. The method involves controlling the air intake end of the nuclear reactor system to be connected to the air intake duct through a pipeline via a control component, thereby enabling the combined engine to enter the nuclear ramjet mode.

[0024] The control components control the air intake end of the nuclear reactor system to connect to the turbine core machine through pipelines, and the combined engine enters the nuclear turbine mode.

[0025] By controlling the air intake end of the nuclear reactor system to connect to the propellant supply system through pipelines via the control components, the combined engine enters the non-breathing mode.

[0026] In one embodiment, the control module controls the first control valve to connect the outlet of the air intake duct to the air intake of the cryogenic nuclear reactor, the second control valve to connect the outlet of the cryogenic nuclear reactor to the air intake of the third control valve, the third control valve to connect the outlet of the third control valve to the air intake of the high-temperature nuclear reactor, the fourth control valve to close, and the fifth control valve to connect the outlet of the high-temperature nuclear reactor to the nozzle inlet of the variable geometry nozzle, so that the combined engine enters the nuclear ramjet mode.

[0027] The control module controls the first control valve to connect the compressor outlet to the cryogenic nuclear reactor inlet, the second control valve to connect the cryogenic nuclear reactor outlet to the high-pressure turbine inlet, the third control valve to connect the low-pressure turbine outlet to the high-temperature nuclear reactor inlet, the fourth control valve to close, and the fifth control valve to connect the high-temperature nuclear reactor outlet to the variable geometry nozzle nozzle inlet, thus enabling the combined engine to enter nuclear turbine mode.

[0028] The control module controls the first control valve to connect the outlet of the working fluid turbine to the inlet of the cryogenic nuclear reactor, the second control valve to connect the outlet of the cryogenic nuclear reactor to the inlet of the third control valve, the third control valve to connect the outlet of the third control valve to the inlet of the high-temperature nuclear reactor, the fourth control valve to open, and the fifth control valve to connect the outlet of the high-temperature nuclear reactor to the nozzle inlet of the regenerative cooling nozzle, so that the combined engine enters the non-intake mode.

[0029] The beneficial effects of this invention are:

[0030] (1) In this invention, the connection relationship of pipelines is controlled by the control component, so as to realize the selective connection between the air intake end of the nuclear reactor system and the air intake duct, the turbine core machine or the propellant supply system, thereby realizing the free switching of three engine modes: ramjet, turbine and non-air intake mode, so that the engine can work in the medium and high speed range, low speed range and in the absence of atmosphere, which can meet the needs of ultra-high speed aircraft for air and space transportation.

[0031] (2) When the combined engine of the present invention is in nuclear turbine mode and nuclear ramjet mode, the propellant is incoming gas. The combined engine itself only consumes nuclear fuel used to maintain the operation of the nuclear reactor. The change in the mass consumed by the engine is small, and it has better specific impulse performance, which can extend the flight time of the spacecraft in the atmosphere. In addition, the combined engine does not consume its own propellant in turbine mode and ramjet mode, which makes the combined engine have high fuel economy. Furthermore, the heating energy of the gas in each mode comes from the nuclear fission process of the nuclear reactor, so the incoming gas does not need to contain oxygen, thereby enabling the spacecraft containing the combined engine of the present invention to achieve extraterrestrial planetary flight. Attached Figure Description

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

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

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

[0035] Figure 4 This is a schematic diagram of the non-intake mode of the combined engine provided in an embodiment of the present invention.

[0036] Explanation of reference numerals in the attached drawings: 100, air intake; 200, first drive shaft; 210, second drive shaft; 220, fan; 230, compressor; 240, high-pressure turbine; 250, low-pressure turbine; 300, working fluid storage tank; 310, working fluid pump; 320, working fluid turbine; 330, third drive shaft; 400, cryogenic 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 Implementation

[0037] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0038] It should be noted that in the description of this invention, "upper," "lower," "top," "bottom," and orientation or positional relationship are based on the appendix. Figure 1 The orientations or positional relationships shown are for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0039] In one embodiment, such as Figure 1 As shown, the combined engine of this embodiment includes a control component and an air intake 100, a turbine core, 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, nuclear reactor system, and propellant supply system are located inside the engine mounting housing, the air intake 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 gas inlet of the nuclear reactor system to be selectively connected to the gas inlet 100, the turbine core, or the propellant supply system via pipelines; the gas outlet of the nuclear reactor system is connected to the nozzle assembly.

[0042] Specifically, when the nuclear reactor system is directly connected to the air intake 100, the combined engine is in nuclear ramjet mode; when the nuclear reactor system is connected to the turbine core, the combined engine is in turbine mode; and when the reactor system is connected to the propellant supply system, the combined engine is in non-breathing mode, i.e., rocket mode, which utilizes propellant combustion to provide propulsion power in a non-breathing state.

[0043] The combined engine in this embodiment can switch between three engine modes: ramjet, turbine, and non-breathing, enabling the engine to operate in medium- and high-speed ranges, low-speed ranges, and even in atmospheric environments, thus meeting the needs of aerospace transportation for aircraft.

[0044] Furthermore, the incoming air from the air intake 100 and the turbine core, as well as the incoming working fluid from the propellant supply system, are heated by a nuclear reactor system and then discharged from the nozzle assembly. The heating energy comes from the nuclear fission process of the reactor. Therefore, the incoming gas does not need to contain oxygen and the engine mass changes less, thereby enabling the aircraft containing the combined engine of this invention to achieve extraterrestrial planetary flight and have better specific impulse performance.

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

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

[0047] Specifically, fan 220 performs first-stage compression on the incoming air from intake duct 100, then directs the compressed air to compressor 230 for further compression. High-pressure turbine 240 receives gas heated by cryogenic nuclear reactor 400 and is driven by this gas to perform work. When rotating, high-pressure turbine 240 provides power to compressor 230 under the drive of second drive shaft 210. The high-temperature air delivered by high-pressure turbine 240 to low-pressure turbine 250 drives low-pressure turbine 250 to perform work, and then low-pressure turbine 250 provides power to fan 220.

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

[0050] To meet the upper limit of the turbine's allowable temperature, in this embodiment, the nuclear reactor system includes a cryogenic nuclear reactor 400 and a high-temperature nuclear reactor 410, used for two-stage heating of the incoming gas or working fluid. The high-temperature nuclear reactor 410 is cylindrical and fitted outside the cryogenic nuclear reactor 400, used for further heating of the incoming gas or working fluid after it has been heated by the cryogenic 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 operating 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 operating conditions of each control valve, thereby realizing different connection relationships with the control valve connecting pipelines and enabling the switching of different engine modes.

[0053] In one embodiment, the outlet of the air inlet 100, the outlet of the compressor 230, and the outlet of the working fluid pump 310 are all connected to the inlet of the first control valve 600, and the inlet of the cryogenic nuclear reactor 400 is connected to the outlet of the first control valve 600.

[0054] The outlet of the cryogenic nuclear reactor 400 is connected to the inlet of the second control valve 610, and the inlet of the high-pressure turbine 240 is connected to the outlet of the second control valve 610.

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

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

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

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

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

[0060] In this embodiment, the air inlet, air outlet, mass feed, and mass outlet are connected via pipelines or directly connected to each other. It should be noted that each control valve can control the connectivity between its connected ports, thereby enabling the switching of different engine modes.

[0061] Based on the same invention, this 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] The control components control the air intake end of the nuclear reactor system to connect to the air intake duct 100 via pipelines, enabling the combined engine to enter the nuclear ramjet mode; the control components control the air intake end of the nuclear reactor system to connect to the turbine core machine via pipelines, enabling the combined engine to enter the nuclear turbine mode; the control components control the air intake end of the nuclear reactor system to connect to the propellant supply system via pipelines, enabling the combined engine to enter the non-breathing mode.

[0063] The method of the present invention can switch the mode of the combined engine according to different speed range requirements to adapt to different flight conditions. It can work in the medium and high speed range, low speed range and atmospheric absence environment, and can meet the needs of aerospace transport aircraft.

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

[0065] Specifically, such as Figure 2 As shown, in ramjet mode, the incoming gas first enters the intake duct 100 for compression. At this time, the turbine core machine system is shut down. The incoming gas passes through the cryogenic nuclear reactor 400 and the high-temperature nuclear reactor 410 in sequence 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 of the compressor 230 to the inlet of the cryogenic nuclear reactor 400, the second control valve 610 to connect the outlet of the cryogenic nuclear reactor 400 to the inlet of the high-pressure turbine 240, the third control valve 620 to connect the outlet of the low-pressure turbine 250 to the inlet of the high-temperature nuclear reactor 410, the fourth control valve 630 to close, and the fifth control valve 640 to connect the outlet of the high-temperature nuclear reactor 410 to the nozzle inlet of the variable geometry nozzle 700, so that the combined engine enters the turbine mode.

[0067] Specifically, such as Figure 3 As shown, in turbine mode, the incoming gas first enters the fan 220 through the intake duct 100. The fan 220 performs a first-stage compression on the incoming gas, and then guides the compressed gas to the compressor 230 for further compression. The compressor 230 then guides the compressed gas into the cryogenic nuclear reactor 400 to increase its temperature. The high-pressure turbine 240 receives the gas heated by the cryogenic nuclear reactor 400 and is driven by it to do work, and provides power to the compressor 230 through the second drive 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. The high-temperature gas drives the low-pressure turbine 250 to do work, and the first drive shaft 200 of the low-pressure turbine 250 provides power to the fan 220. 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 of the working fluid turbine 320 to the inlet of the cryogenic nuclear reactor 400, the second control valve 610 to connect the outlet of the cryogenic nuclear reactor 400 to the inlet of the third control valve 620, the third control valve 620 to connect the outlet of the third control valve 620 to 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 to the nozzle inlet of the regenerative cooling nozzle 710, so that the combined engine enters the non-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, such as Figure 4 As shown, in the non-intake mode, both the intake duct 100 and the turbine core are closed, and the combined engine uses the propellant stored in the propellant storage tank 300. The propellant is drawn from the propellant storage tank 300 and pressurized by the propellant pump 310. Then, the propellant is divided into two streams. The first stream of propellant first passes through the regenerative cooling nozzle 710 to cool the nozzle, and in the process, it becomes gaseous. The gaseous propellant then enters the propellant turbine 320 to drive it to do work. The second stream of propellant flows directly through the cryogenic nuclear reactor 400 to be heated and form a gaseous propellant. Then, the first and second gaseous propellants are mixed and flow together through the high-temperature nuclear reactor 410 for further heating before being introduced into the regenerative cooling nozzle 710 and ejected to generate thrust.

[0071] It should be noted that in a vacuum environment, nozzle heat dissipation is difficult, and excessively high nozzle temperatures may lead to nozzle melting or structural damage. In this embodiment, a regenerative cooling nozzle is used, employing liquid working fluid to cool the regenerative cooling nozzle and prevent damage. Furthermore, in non-intake mode, the cooling channel of the regenerative cooling nozzle cannot fully accommodate all the propellant; therefore, the propellant needs to be split into two streams. One stream enters the regenerative cooling channel. Since the liquid working fluid changes to a gaseous state upon passing through the cooling channel, the other stream is first heated to a gaseous state by a cryogenic nuclear reactor to avoid the complex situation of gas-liquid mixing when the two streams are mixed.

[0072] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. A combined engine characterized in that, It includes control components and, via piping, an air intake (100), a turbine core, a nuclear reactor system, a propellant supply system, and nozzle assemblies; The control component is used to control the air intake end of the nuclear reactor system to be selectively connected to the air intake duct (100), the turbine core, or the propellant supply system via pipelines. The gas outlet of the nuclear reactor system is connected to the nozzle assembly; The turbine core is equipped with a first drive shaft (200), a second drive 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 drive shaft (200), and the compressor (230) and the high-pressure turbine (240) are connected via a second drive shaft (210). The first drive shaft (200) and the second drive shaft (210) are coaxial. The air inlet of the fan (220) is connected to the air outlet of the air inlet (100), the air inlet of the compressor (230) is connected to the air outlet of the fan (220), and the air outlet of the high-pressure turbine (240) is connected to the air inlet of the low-pressure turbine (250). The propellant supply system includes a working propellant storage tank (300), a working propellant pump (310), and a working propellant turbine (320). The inlet end of the working propellant pump (310) is connected to the outlet end of the working propellant storage tank (300), and the working propellant turbine (320) is connected to the working propellant pump (310) via a third drive shaft (330). The nuclear reactor system includes a low-temperature nuclear reactor (400) and a high-temperature nuclear reactor (410), wherein the high-temperature nuclear reactor (410) is cylindrical and is fitted outside the low-temperature nuclear reactor (400); The 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 operating conditions of each control valve. The nozzle assembly includes a variable geometry nozzle (700) and a regenerative cooling nozzle (710).

2. The combination engine of claim 1, wherein, The outlet of the air inlet (100), the outlet of the compressor (230), and the outlet of the working fluid pump (310) are all connected to the inlet of the first control valve (600), and the inlet of the cryogenic nuclear reactor (400) is connected to the outlet of the first control valve (600). The outlet of the cryogenic nuclear reactor (400) is connected to the inlet of the second control valve (610), and the inlet of the high-pressure turbine (240) is connected to the outlet of the second control valve (610). The outlet of the second control valve (610) and the outlet of the low-pressure turbine (250) are both connected to the inlet of the third control valve (620). The outlet of the third control valve (620) is connected to the inlet of the high-temperature nuclear reactor (410), and the outlet of the high-temperature nuclear reactor (410) is connected to the inlet of the fifth control valve (640). The nozzle inlets of both the variable geometry nozzle (700) and the regenerative cooling nozzle (710) are connected to the outlet of the fifth control valve (640). The outlet of the working fluid turbine (320) is connected to the inlet of the fourth control valve (630), and the outlet of the fourth control valve (630) is connected to the inlet of the high-temperature nuclear reactor (410). The cooling channel inlet of the regenerating cooling nozzle (710) is connected to the outlet end of the working fluid pump (310), and the cooling channel outlet of the regenerating cooling nozzle (710) is connected to the inlet end of the working fluid turbine (320).

3. A combined engine control method for controlling the combined engine according to any one of claims 1 to 2 into different working modes, characterized in that, The combined engine enters the nuclear ramjet mode by controlling the air intake end of the nuclear reactor system to be connected to the air intake duct (100) through a pipeline by the control component. The combined engine enters nuclear turbine mode by controlling the air intake end of the nuclear reactor system to be connected to the turbine core machine through a pipeline via the control components. By controlling the air intake end of the nuclear reactor system to connect to the propellant supply system through pipelines via the control components, the combined engine enters the non-air-breathing mode.

4. The combined engine control method according to claim 3, characterized by, The combined engine enters nuclear ramjet mode by controlling the first control valve (600) to connect the outlet of the air intake (100) to the air intake of the cryogenic nuclear reactor (400), the second control valve (610) to connect the outlet of the cryogenic nuclear reactor (400) to the air intake of the third control valve (620), the third control valve (620) to connect the outlet of the third control valve (620) to the air intake of the high-temperature nuclear reactor (410), the fourth control valve (630) to close, and the fifth control valve (640) to connect the outlet of the high-temperature nuclear reactor (410) to the nozzle inlet of the variable geometry nozzle (700). The combined engine enters nuclear turbine mode by controlling the first control valve (600) to connect the outlet of the compressor (230) to the inlet of the cryogenic nuclear reactor (400), the second control valve (610) to connect the outlet of the cryogenic nuclear reactor (400) to the inlet of the high-pressure turbine (240), the third control valve (620) to connect the outlet of the low-pressure turbine (250) to the inlet of the high-temperature nuclear reactor (410), the fourth control valve (630) to close, and the fifth control valve (640) to connect the outlet of the high-temperature nuclear reactor (410) to the nozzle inlet of the variable geometry nozzle (700). The combined engine enters a non-intake mode by controlling the first control valve (600) to connect the outlet of the working fluid turbine (320) to the inlet of the cryogenic nuclear reactor (400), the second control valve (610) to connect the outlet of the cryogenic nuclear reactor (400) to the inlet of the third control valve (620), the third control valve (620) to connect the outlet of the third control valve (620) to 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) to the nozzle inlet of the regenerative cooling nozzle (710).

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