CN120062001A - Combined engine and control method thereof - Google Patents
Combined engine and control method thereof Download PDFInfo
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- CN120062001A CN120062001A CN202510085204.8A CN202510085204A CN120062001A CN 120062001 A CN120062001 A CN 120062001A CN 202510085204 A CN202510085204 A CN 202510085204A CN 120062001 A CN120062001 A CN 120062001A
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- control valve
- nuclear reactor
- air inlet
- outlet end
- air outlet
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K27/00—Plants for converting heat or fluid energy into mechanical energy, not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
- F01K7/16—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines being only of turbine type
- F01K7/22—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines being only of turbine type the turbines having inter-stage steam heating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
- F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
- F02C1/05—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
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- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21D—NUCLEAR POWER PLANT
- G21D5/00—Arrangements of reactor and engine in which reactor-produced heat is converted into mechanical energy
- G21D5/02—Reactor and engine structurally combined, e.g. portable
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- High Energy & Nuclear Physics (AREA)
- Plasma & Fusion (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a combined engine and a control method thereof, wherein 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 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 machine or the propellant supply system through a pipeline, and the air outlet end of the nuclear reactor system is connected with the spray pipe assembly. The control assembly is used for controlling the air inlet end of the nuclear reactor system to be respectively connected with the air inlet channel, the turbine core machine and the propellant supply system through pipelines, so that the combined engine can respectively enter a nuclear punching mode, a nuclear turbine mode and a non-air-suction mode. The invention has the characteristics of high fuel economy, capability of working in an atmospheric environment, capability of realizing flight in different speed ranges by adopting different engine modes, and capability of meeting the requirement of the ultra-high speed aircraft on air-to-day transportation.
Description
Technical Field
The invention relates to the technical field of aircraft engines, in particular to a combined engine and a control method thereof.
Background
The main function of the aircraft engine is to provide propulsion power or support force for the aircraft, which is the core component of the aircraft. Existing aircraft engines can be categorized into turbine engines, ramjet engines, and non-air-breathing engines, each of which has its own operating speed range.
In order to achieve wide speed range flight of engines, the prior art combines different engines to form a combined engine. The combined engine is an engine formed by combining two or more engines with different working modes, and has a wider working speed range. In recent years, the related technology of the combined engine is developed faster, and a new alternative power system is provided for an ultra-high-speed aircraft and the like from an early non-suction and ramjet combined cycle engine and a turbine-based ramjet combined cycle engine to the current air turbine ramjet combined engine and the like.
However, the jet injection effect of the non-air-suction and stamping combined cycle engine is utilized to make up for the shortage of stamping compression capacity of a low-speed section, too much propellant is consumed in the process of accelerating the engine to Mach number of stamping mode operation, the fuel economy is low, the turbine-based stamping combined cycle engine is difficult to coordinate and design and cannot work in an environment without atmosphere, and the upper limit of the flying speed of the air turbine stamping combined engine cannot meet the requirement of the ultra-high-speed aircraft for air-to-air transportation.
Disclosure of Invention
Based on the above, it is necessary to provide a combined engine and a control method thereof, which have high fuel economy, can work in an atmospheric environment, can adopt different engine modes to realize different speed ranges for flight, and can meet the requirement of the ultra-high speed aircraft for aerospace transportation.
In a first aspect, the present invention provides a combined engine comprising a control assembly and an inlet duct, a turbine core, a nuclear reactor system, a propellant supply system and a nozzle assembly connected by piping;
the control component 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 machine or the propellant supply system through a pipeline;
the gas outlet end of the nuclear reactor system is connected to the nozzle assembly.
In one embodiment, the turbine core is provided with a first drive shaft, a second drive shaft, a fan, a compressor, a high pressure turbine and a low pressure turbine;
The fan is connected with the low-pressure turbine through a first transmission shaft, the air compressor is connected with the high-pressure turbine through a second transmission shaft, and the first transmission shaft and the second transmission shaft are coaxial;
The air inlet end of the fan is connected with the air outlet end of the air inlet channel, the air inlet end of the air compressor is connected with the air outlet end of the fan, and the air outlet end of the high-pressure turbine is connected with the air inlet end of the low-pressure turbine.
In one embodiment, the propellant supply system comprises a working medium storage tank, a working medium pump and a working medium turbine, wherein the material inlet end of the working medium pump is connected with the material outlet end of the working medium storage tank, and the working medium turbine is connected with the working medium pump through a third transmission shaft.
In one embodiment, the nuclear reactor system comprises a low temperature nuclear reactor and a high temperature nuclear reactor, wherein the high temperature nuclear reactor is cylindrical and sleeved outside the low temperature nuclear reactor.
In one embodiment, the pipeline control assembly comprises 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 condition of each control valve;
The nozzle assembly includes a variable geometry nozzle and a regeneratively cooled nozzle.
In one embodiment, the air outlet end of the air inlet channel, the air outlet end of the air compressor and the air outlet end of the working medium pump are all connected with the air inlet end of the first control valve, and the air inlet end of the low-temperature nuclear reactor is connected with the air outlet end of the first control valve;
the air outlet end of the low-temperature nuclear reactor is connected with the air inlet end of the second control valve, and the air inlet end of the high-pressure turbine is connected with the air outlet end of the second control valve;
The air outlet end of the second control valve and the air outlet end of the low-pressure turbine are connected with the air inlet end of the third control valve;
The air outlet end of the third control valve is connected with the air inlet end of the high-temperature nuclear reactor, and the air outlet end of the high-temperature nuclear reactor is connected with the air inlet end of the fifth control valve;
The nozzle inlets of the variable geometry nozzle and the regenerative cooling nozzle are connected with the air outlet end of the fifth control valve;
the air outlet end of the working medium turbine is connected with the air inlet end of the fourth control valve, and the air outlet end of the fourth control valve is connected with the air inlet end of the high-temperature nuclear reactor;
the cooling channel inlet of the regenerative cooling spray pipe is connected with the quality outlet end of the working medium pump, and the cooling channel outlet of the regenerative cooling spray pipe is connected with the air inlet end of the working medium turbine.
In a second aspect, the present invention further provides a control method for controlling the above-mentioned combined engine to enter different working modes, wherein the control component is used for controlling the air inlet end of the nuclear reactor system to be connected with the air inlet channel through a pipeline, and the combined engine enters a nuclear punching mode;
The control assembly is used for controlling the air inlet end of the nuclear reactor system to be connected with the turbine core machine through a pipeline, and the combined engine enters a nuclear turbine mode;
the control assembly controls the air inlet end of the nuclear reactor system to be connected with the propellant supply system through a pipeline, and the combined engine enters a non-inhalation mode.
In one embodiment, a control module is used for controlling a first control valve to be connected with an air outlet end of an air inlet channel and an air inlet end of a low-temperature nuclear reactor, a second control valve to be connected with an air outlet end of the low-temperature nuclear reactor and an air inlet end of a third control valve, the third control valve to be connected with an air outlet end of the third control valve and an air inlet end of a high-temperature nuclear reactor, a fourth control valve to be closed, a fifth control valve to be connected with an air outlet end of the high-temperature nuclear reactor and a jet pipe inlet of a variable geometry jet pipe, and a combined engine enters a nuclear stamping mode;
The control module is used for controlling the first control valve to be connected with the gas outlet end of the gas compressor and the gas inlet end of the low-temperature nuclear reactor, the second control valve to be connected with the gas outlet end of the low-temperature nuclear reactor and the gas inlet end of the high-pressure turbine, the third control valve to be connected with the gas outlet end of the low-pressure turbine and the gas inlet end of the high-temperature nuclear reactor, the fourth control valve to be closed, the fifth control valve to be connected with the gas outlet end of the high-temperature nuclear reactor and the nozzle inlet of the variable geometry nozzle, and the combined engine enters a nuclear turbine mode;
The control module is used for controlling the first control valve to be connected with the air outlet end of the working medium turbine and the air inlet end of the low-temperature nuclear reactor, the second control valve to be connected with the air outlet end of the low-temperature nuclear reactor and the air inlet end of the third control valve, the third control valve to be connected with the air outlet end of the third control valve and the air inlet end of the high-temperature nuclear reactor, the fourth control valve to be opened, the fifth control valve to be connected with the air outlet end of the high-temperature nuclear reactor and the spray pipe inlet of the regeneration cooling spray pipe, and the combined engine enters a non-air suction mode.
The beneficial effects of the invention are as follows:
(1) According to the invention, the control assembly controls the pipeline communication relation, so that the alternative selective connection of the air inlet end of the nuclear reactor system and the air inlet channel, the turbine core engine or the propellant supply system is realized, and the free switching of three engine modes of stamping, turbine and non-air-suction modes is further realized, so that the engine can work in a medium-high speed section, a low speed section and an atmospheric-free environment, and the requirement of the ultra-high speed aircraft on air-sky transportation can be met.
(2) When the combined engine is in a nuclear turbine mode and a nuclear stamping mode, a propelling working medium is used as incoming gas, the combined engine only consumes nuclear fuel for maintaining the operation of a nuclear reactor, the engine consumption quality change is small, the combined engine has better specific impact performance, the flight time of an aircraft in the atmosphere can be prolonged, the combined engine has higher fuel economy due to the fact that the combined engine does not consume the carrying working medium in the turbine mode and the stamping mode, in addition, the heating energy of each mode gas is derived from the nuclear fission process of the nuclear reactor, oxygen is not needed to be contained in the incoming gas, and the aircraft comprising the combined engine can realize the extraterrestrial planet flight.
Drawings
FIG. 1 is a schematic view of a combined engine according to an embodiment of the present invention;
Fig. 2 is a schematic diagram of a stamping mode of a combined engine according to an embodiment of the present invention;
FIG. 3 is a schematic view of a turbine mode of a combined engine according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a non-air-suction mode of a combined engine according to an embodiment of the present invention.
The reference numerals are 100, an air inlet, 200, a first transmission shaft, 210, a second transmission shaft, 220, a fan, 230, a gas compressor, 240, a high-pressure turbine, 250, a low-pressure turbine, 300, a working medium storage box, 310, a working medium pump, 320, a working medium turbine, 330, a third transmission shaft, 400, a low-temperature nuclear reactor, 410, a high-temperature nuclear reactor, 600, a first control valve, 610, a second control valve, 620, a third control valve, 630, a fourth control valve, 640, a fifth control valve, 700, a variable geometry spray pipe, 710 and a regenerative cooling spray pipe.
Detailed Description
In order that the above objects, features and advantages of the invention will be readily understood, a more particular description of the invention will be rendered by reference to the appended drawings.
It should be noted that, in the description of the present invention, the terms "upper," "lower," "top," "bottom," and orientation or positional relationship are based on the orientation or positional relationship shown in fig. 1, and it should be understood that these terms are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements to be referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
In one embodiment, as shown in FIG. 1, the combined engine of the present embodiment includes a control assembly and an inlet port 100, a turbine core, a nuclear reactor system, a propellant supply system, and a nozzle assembly connected by piping.
In the present embodiment, the turbine core, the nuclear reactor system, and the propellant supply system are located inside the engine mounting case, the intake duct 100 is located at the front end of the case, and the nozzle assembly is located at the rear end of the case.
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 100, the turbine core machine or the propellant supply system through a pipeline, and the air outlet end of the nuclear reactor system is connected with the spray pipe assembly.
Specifically, when the nuclear reactor system is directly connected to the air inlet duct 100, the combined engine is in a nuclear punching mode, when the nuclear reactor system is connected to the turbine core, the combined engine is in a turbine mode, and when the reactor system is connected to the propellant supply system, the combined engine is in a non-air-intake mode, namely, a rocket mode, and propulsion power is provided in a non-air-intake state by using propellant combustion.
The combined engine of the embodiment can realize the switching of the stamping mode, the turbine mode and the non-air-suction mode, so that the engine can work in a medium-high speed section, a low speed section and an atmospheric environment, and the air-to-air transportation requirement of an aircraft can be met.
In addition, for the incoming air of the air inlet channel 100 and the turbine core machine, and the incoming working medium of the propellant supply system, the incoming air is heated by the nuclear reactor system and then discharged from the nozzle assembly, and the heating energy is derived from the nuclear fission process of the reactor, so that the incoming air does not need to contain oxygen and the engine quality is less in change, and the aircraft comprising the combined engine can realize the extraterrestrial planetary flight and has better specific impact performance.
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.
The fan 220 is connected with the low-pressure turbine 250 through the first transmission shaft 200, the compressor 230 is connected with the high-pressure turbine 240 through the second transmission shaft 210, the first transmission shaft 200 and the second transmission shaft 210 are coaxial, the air inlet end of the fan 220 is connected with the air outlet end of the air inlet channel 100, the air inlet end of the compressor 230 is connected with the air outlet end of the fan 220, and the air outlet end of the high-pressure turbine 240 is connected with the air inlet end of the low-pressure turbine 250.
Specifically, the fan 220 is configured to perform a first stage of compression on the incoming air of the inlet 100, and then direct the compressed air to the compressor 230 for further compression. The high-pressure turbine 240 is capable of receiving the gas heated by the low-temperature nuclear reactor 400 and is pushed by the gas to perform work. The high-pressure turbine 240, when rotated, powers the compressor 230 under the drive of the second drive shaft 210. The high-temperature air delivered by the high-pressure turbine 240 to the low-pressure turbine 250 pushes the low-pressure turbine 250 to perform work, and then the low-pressure turbine 250 powers the fan 220.
In one embodiment, the propellant supply system includes a working medium storage tank 300, a working medium pump 310, and a working medium turbine 320, wherein the inlet end of the working medium pump 310 is connected to the outlet end of the working medium storage tank 300, and the working medium turbine 320 is connected to the working medium pump 310 through a third transmission shaft 330.
Specifically, the working medium storage tank 300 may store working medium 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 shaft, the working fluid turbine 320 is configured to power the working fluid pump 310.
To meet the upper allowable temperature limit of the turbine, in the present embodiment, the nuclear reactor system includes a low temperature nuclear reactor 400 and a high temperature nuclear reactor 410 for two-stage heating of the incoming gas or working fluid. The high-temperature nuclear reactor 410 is cylindrical, is sleeved outside the low-temperature nuclear reactor 400, and is used for further heating the inflow gas or working medium after the low-temperature nuclear reactor 400 is heated.
In one embodiment, 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 operation of each control valve, and the nozzle assembly comprises a variable geometry nozzle 700 and a regenerative cooling nozzle 710.
In this embodiment, the control module can control the working condition of each control valve, and then realize the different relation of connection with the control valve communication pipeline, realize the switching of different modes of engine.
In one embodiment, the air outlet end of the air inlet 100, the air outlet end of the air compressor 230 and the air outlet end of the working medium 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 with the gas inlet end of the second control valve 610, and the gas inlet end of the high-pressure turbine 240 is connected with 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 with the air inlet end of the third control valve 620;
The air outlet end of the third control valve 620 is connected with the air inlet end of the high temperature nuclear reactor 410, and the air outlet end of the high temperature nuclear reactor 410 is connected with the air inlet end of the fifth control valve 640;
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;
The gas outlet end of the working fluid turbine 320 is connected with the gas inlet end of the fourth control valve 630, and the gas outlet end of the fourth control valve 630 is connected with 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 inlet end of the working fluid turbine 320.
The air inlet end, the air outlet end, the air inlet end and the air outlet end in the embodiment are directly connected through pipeline connection or parts. It should be noted that, each control valve may control connectivity between ports connected to the control valve, so as to enable switching between different modes of the combined engine.
Based on the same invention, the invention also provides a combined engine control method for controlling the combined engine in any one of the embodiments to enter different working modes, which specifically comprises the following steps:
The control assembly controls the air inlet end of the nuclear reactor system to be connected with the air inlet channel 100 through a pipeline so that the combined engine enters a nuclear punching mode, the control assembly controls the air inlet end of the nuclear reactor system to be connected with the turbine core machine through a pipeline so that the combined engine enters a nuclear turbine mode, and the control assembly controls the air inlet end of the nuclear reactor system to be connected with the propellant supply system through a pipeline so that the combined engine enters a non-inhalation mode.
The method can switch the modes of the combined engine according to different speed domain requirements so as to be suitable for different flight conditions, can work in medium-high speed sections, low speed sections and no atmosphere environment, and can meet the requirements of an air-sky transport aircraft.
In one embodiment, the control module controls the first control valve 600 to connect the air outlet end of the air inlet channel 100 with the air inlet end of the low-temperature nuclear reactor 400, the second control valve 610 to connect the air 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 air 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, the fifth control valve 640 to connect the air outlet end of the high-temperature nuclear reactor 410 with the nozzle inlet of the variable geometry nozzle 700, and the combined engine enters a stamping mode.
Specifically, as shown in fig. 2, in the stamping mode, the incoming gas first enters the air inlet channel 100 for compression, at this time, the turbine core system is closed, the incoming gas sequentially passes through the low-temperature nuclear reactor 400 and the high-temperature nuclear reactor 410 for heating, and then is directly ejected through the variable geometry nozzle 700 for generating thrust.
The control module controls the first control valve 600 to switch on the air outlet end of the compressor 230 and the air inlet end of the low-temperature nuclear reactor 400, the second control valve 610 to switch on the air outlet end of the low-temperature nuclear reactor 400 and the air inlet end of the high-pressure turbine 240, the third control valve 620 to switch on the air outlet end of the low-pressure turbine 250 and the air inlet end of the high-temperature nuclear reactor 410, the fourth control valve 630 to be closed, the fifth control valve 640 to switch on the air outlet end of the high-temperature nuclear reactor 410 and the nozzle inlet of the variable geometry nozzle 700, and the combined engine enters a turbine mode.
Specifically, as shown in fig. 3, in the turbo mode, the incoming gas enters the fan 220 through the air inlet 100, the fan 220 compresses the incoming gas for the first stage, the compressed gas is then led to the compressor 230 for further compression, the compressor 230 re-introduces the compressed gas into the low-temperature nuclear reactor 400 for temperature increase, the high-pressure turbine 240 receives the gas heated by the low-temperature nuclear reactor 400 and is pushed by the gas to apply work, and the high-pressure turbine 240 provides power for the compressor 230 through the second transmission shaft 210, the high-temperature gas heated by the low-temperature nuclear reactor 400 is led into the low-pressure turbine 250, the high-temperature gas pushes the low-pressure turbine 250 to apply work, the first transmission shaft 200 of the low-pressure turbine 250 provides power for the fan 220, and finally the air is ejected through the variable geometry nozzle 700 to generate thrust.
The control module controls the first control valve 600 to connect the air outlet end of the working medium turbine 320 with the air inlet end of the low-temperature nuclear reactor 400, the second control valve 610 to connect the air 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 air 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 open, the fifth control valve 640 to connect the air outlet end of the high-temperature nuclear reactor 410 with the nozzle inlet of the regenerative cooling nozzle 710, and the combined engine enters a non-air-suction mode.
It should be noted that only when fourth control valve 630 is activated, the cooling passage of regenerative cooling lance 710 is activated.
Specifically, as shown in fig. 4, in the non-air-suction mode, both the air inlet 100 and the turbine core are in a closed state, and the combined engine works by using the propulsion working medium in the working medium storage tank 300. The working medium is pumped out from the working medium storage box 300 by the working medium pump 310 and pressurized, then the working medium is divided into two streams, the first stream of working medium firstly cools the jet pipe through the regenerative cooling jet pipe 710, the first stream of working medium is cooled and is changed into a gas state, the gas state working medium enters the working medium turbine 320 again to push the working medium to do work, the second stream of working medium directly flows through the low-temperature nuclear reactor 400 to heat the working medium to form the gas state working medium, and then the first stream of working medium and the second stream of working medium are mixed and then jointly flow through the high-temperature nuclear reactor 410 to be further heated, and then the working medium is led into the regenerative cooling jet pipe 710 to be ejected to generate thrust.
It should be noted that, in a vacuum environment, the heat dissipation of the nozzle is difficult, and when the temperature of the nozzle is too high, the nozzle may melt or be damaged in structure. The spray pipe in the embodiment adopts a regenerative cooling spray pipe, and the liquid working substance is utilized to cool the regenerative cooling spray pipe, so that the spray pipe is prevented from being damaged. In addition, in the non-air-suction mode, the cooling channel of the regenerative cooling spray pipe cannot completely receive all the propelling working medium, the propelling working medium needs to be split into two streams, and one stream of working medium enters the regenerative cooling channel. Because the liquid working medium passing through the cooling channel is changed into the gaseous state, the other working medium is heated into the gaseous state by the low-temperature nuclear reactor, and the complex condition of gas-liquid mixing generated when the two working media are mixed is avoided.
The foregoing examples illustrate only a few embodiments of the invention and are described in detail herein without thereby limiting the scope of the invention. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of the invention should be assessed as that of the appended claims.
Claims (8)
1. A combined engine, characterized by comprising a control assembly and an air inlet channel (100), a turbine core, a nuclear reactor system, a propellant supply system and a nozzle assembly which are connected by pipelines;
The control assembly is used for controlling the air inlet end of the nuclear reactor system to be selectively connected with an air inlet channel (100), a turbine core machine or a propellant supply system through a pipeline;
the gas outlet end of the nuclear reactor system is coupled to the nozzle assembly.
2. The combined engine according to claim 1, characterized in that 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);
the fan (220) is connected with the low-pressure turbine (250) through a first transmission shaft (200), the compressor (230) and the high-pressure turbine (240) are connected through 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 with the air outlet end of the air inlet channel (100), the air inlet end of the air compressor (230) is connected with the air outlet end of the fan (220), and the air outlet end of the high-pressure turbine (240) is connected with the air inlet end of the low-pressure turbine (250).
3. The combined engine of claim 2, wherein the propellant supply system comprises 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) being connected to the outlet end of the working fluid storage tank (300), the working fluid turbine (320) being connected to the working fluid pump (310) by a third drive shaft (330).
4. The combined engine of claim 3, wherein the nuclear reactor system comprises a low temperature nuclear reactor (400) and a high temperature nuclear reactor (410), the high temperature nuclear reactor (410) being tubular and being sleeved outside the low temperature nuclear reactor (400).
5. The combined engine of claim 4, wherein the line 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 operation of each control valve;
the nozzle assembly includes a variable geometry nozzle (700) and a regenerative cooling nozzle (710).
6. The combined engine of claim 5, wherein the air outlet end of the air inlet channel (100), the air outlet end of the air compressor (230) and the quality outlet end of the working medium pump (310) are all connected with the air inlet end of the first control valve (600), and the air inlet end of the low-temperature nuclear reactor (400) is connected with the air outlet end of the first control valve (600);
The air outlet end of the low-temperature nuclear reactor (400) is connected with the air inlet end of the second control valve (610), and the air inlet end of the high-pressure turbine (240) is connected with the air 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 connected with the air inlet end of the third control valve (620);
The air outlet end of the third control valve (620) is connected with the air inlet end of the high-temperature nuclear reactor (410), and the air outlet end of the high-temperature nuclear reactor (410) is connected with the air inlet end of the fifth control valve (640);
The nozzle inlets of the variable geometry nozzle (700) and the regenerative cooling nozzle (710) are connected with the air outlet end of the fifth control valve (640);
The air outlet end of the working medium turbine (320) is connected with the air inlet end of the fourth control valve (630), and the air outlet end of the fourth control valve (630) is connected with the air inlet end of the high-temperature nuclear reactor (410);
The cooling channel inlet of the regenerative cooling spray pipe (710) is connected with the outlet end of the working medium pump (310), and the cooling channel outlet of the regenerative cooling spray pipe (710) is connected with the air inlet end of the working medium turbine (320).
7. A method of controlling a combined engine for controlling the combined engine as claimed in any one of claims 1 to 6 into different modes of operation, wherein the control assembly is used to control the inlet end of the nuclear reactor system to be connected to an inlet channel (100) via a pipeline, the combined engine being arranged to enter a nuclear punching mode;
The air inlet end of the nuclear reactor system is controlled by a control assembly to be connected with a turbine core machine through a pipeline, and the combined engine enters a nuclear turbine mode;
and controlling the air inlet end of the nuclear reactor system to be connected with a propellant supply system through a pipeline by a control assembly, wherein the combined engine enters a non-inspiration mode.
8. The combined engine control method according to claim 7, characterized in that the combined engine enters a nuclear stamping mode by controlling a first control valve (600) to switch on an air outlet end of the air inlet channel (100) and an air inlet end of the low-temperature nuclear reactor (400), a second control valve (610) to switch on an air outlet end of the low-temperature nuclear reactor (400) and an air inlet end of a third control valve (620), a third control valve (620) to switch on an air outlet end of the third control valve (620) and an air inlet end of the high-temperature nuclear reactor (410), a fourth control valve (630) to be closed, a fifth control valve (640) to switch on an air outlet end of the high-temperature nuclear reactor (410) and a nozzle inlet of the variable geometry nozzle (700) by a control module;
The control module is used for controlling a first control valve (600) to be connected with the air outlet end of the compressor (230) and the air inlet end of the low-temperature nuclear reactor (400), a second control valve (610) to be connected with the air outlet end of the low-temperature nuclear reactor (400) and the air inlet end of the high-pressure turbine (240), a third control valve (620) to be connected with the air outlet end of the low-pressure turbine (250) and the air inlet end of the high-temperature nuclear reactor (410), a fourth control valve (630) to be closed, a fifth control valve (640) to be connected with the air outlet end of the high-temperature nuclear reactor (410) and the nozzle inlet of the variable geometry nozzle (700), and the combined engine enters a nuclear turbine mode;
The control module is used for controlling the first control valve (600) to be connected with the air outlet end of the working medium turbine (320) and the air inlet end of the low-temperature nuclear reactor (400), the second control valve (610) to be connected with the air outlet end of the low-temperature nuclear reactor (400) and the air inlet end of the third control valve (620), the third control valve (620) to be connected with the air outlet end of the third control valve (620) and the air inlet end of the high-temperature nuclear reactor (410), the fourth control valve (630) to be opened, the fifth control valve (640) to be connected with the air outlet end of the high-temperature nuclear reactor (410) and the jet pipe inlet of the regeneration cooling jet pipe (710), and the combined engine enters a non-air-suction mode.
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| US20240229744A1 (en) * | 2023-01-05 | 2024-07-11 | Ajay P. Kothari | High Speed Aircraft Propelled by Thorium or Uranium Fueled Molten Salt Reactor |
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| GB1029840A (en) * | 1961-10-25 | 1966-05-18 | Kershaw H A | Improvements in thermal engins, for example gas turbine engines, jet propulsion units and engins powered by nuclear reactors |
| US3630022A (en) * | 1968-09-14 | 1971-12-28 | Rolls Royce | Gas turbine engine power plants |
| DE1817255A1 (en) * | 1968-12-27 | 1970-07-09 | Clarke Chapman Ltd | Power plant having increased output - using gas cooled reactor |
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