CN109677639B - Space high-power nuclear power system based on closed Brayton cycle - Google Patents
Space high-power nuclear power system based on closed Brayton cycle Download PDFInfo
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- CN109677639B CN109677639B CN201811649546.4A CN201811649546A CN109677639B CN 109677639 B CN109677639 B CN 109677639B CN 201811649546 A CN201811649546 A CN 201811649546A CN 109677639 B CN109677639 B CN 109677639B
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 41
- 230000017525 heat dissipation Effects 0.000 claims abstract description 26
- AFAUWLCCQOEICZ-UHFFFAOYSA-N helium xenon Chemical compound [He].[Xe] AFAUWLCCQOEICZ-UHFFFAOYSA-N 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 claims description 61
- 229910052734 helium Inorganic materials 0.000 claims description 44
- 239000001307 helium Substances 0.000 claims description 44
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 40
- 238000010438 heat treatment Methods 0.000 claims description 14
- 238000004880 explosion Methods 0.000 claims description 12
- 230000005855 radiation Effects 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 9
- 229910052724 xenon Inorganic materials 0.000 claims description 8
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 claims description 6
- 239000007788 liquid Substances 0.000 claims description 6
- 239000003638 chemical reducing agent Substances 0.000 claims description 5
- 239000012530 fluid Substances 0.000 claims description 5
- 239000000110 cooling liquid Substances 0.000 claims description 4
- 239000002826 coolant Substances 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims 1
- 230000033228 biological regulation Effects 0.000 abstract description 13
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 238000000605 extraction Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 238000004140 cleaning Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/408—Nuclear spacecraft propulsion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/421—Non-solar power generation
- B64G1/422—Nuclear power generation
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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
- F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
- F01K25/06—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using mixtures of different fluids
Abstract
The invention provides a space high-power nuclear power system based on closed Brayton cycle, which comprises: the system comprises a space nuclear reactor, a Brayton thermoelectric conversion subsystem, a heat dissipation subsystem, a circulating working medium storage and supply subsystem, a reactor auxiliary heat dissipation subsystem, an electric propulsion subsystem and an electric load subsystem. The helium-xenon mixed gas is used as a circulating working medium to realize high-efficiency thermoelectric conversion, and a high-voltage direct-driven high-specific-impulse high-thrust electric thruster is used for high-efficiency propulsion. The system solves the problems of high-efficiency thermoelectric conversion of the nuclear power aircraft, unmatched high voltage of the motor end and low voltage of the electric thruster and large-range electric power regulation.
Description
Technical Field
The invention relates to the field of aircraft power systems, in particular to a space high-power nuclear power system based on closed Brayton cycle.
Background
At present, the space nuclear power aircraft mainly utilizes isotope decay, and a small part of nuclear power supply of a reactor is still in a low-power range within kilowatt level. Meanwhile, in the thermoelectric conversion mode, static conversion such as thermocouple and thermion is still used as a main mode, and the thermoelectric conversion efficiency is not more than 10%. With the continuous development of aerospace technology, the spacecraft has a development trend of load diversification and task complication, the equipment composition of the spacecraft is more and more complex, and the requirement on energy is gradually developed to hundreds of kilowatts and even megawatts. Therefore, it is necessary to develop a high-power and high-efficiency nuclear power system to meet the increasingly severe requirements of the aircraft on energy and power.
At present, no description or report of similar technologies to the technology of the invention is found at home, and similar data at home and abroad is not collected.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a space high-power nuclear power system based on a closed Brayton cycle.
The invention provides a space high-power nuclear power system based on closed Brayton cycle, which comprises: the system comprises a space nuclear reactor, a Brayton thermoelectric conversion subsystem, a heat dissipation subsystem, a circulating working medium storage and supply subsystem, a reactor auxiliary heat dissipation subsystem, an electric propulsion subsystem and an electric load subsystem;
the temperature of a circulating working medium of the Brayton thermoelectric conversion subsystem is increased by the space nuclear reactor through an internal heating pipeline, a turbine in the thermoelectric conversion subsystem converts the heat energy of the high-temperature and high-pressure circulating working medium into shaft power, part of the shaft power is used for driving a gas compressor to complete the circulating pressurization of the working medium, and surplus shaft power drives a generator to output electric energy; the Brayton thermoelectric conversion subsystem is respectively connected with the heat dissipation subsystem, the circulating working medium storage and supply subsystem, the electric propulsion subsystem and the electric load subsystem through a pipeline I, a pipeline II, a cable I and a cable II.
Preferably, the space nuclear reactor is a megawatt-level small space reactor, and helium or helium-xenon mixed gas is used as a heat carrier to lead out heat inside the reactor.
Preferably, the brayton thermoelectric conversion subsystem comprises a heating pipe, a turbine, a gas compressor, a generator, a heat regenerator, a cooler, a bypass valve, a temperature sensor, a pressure sensor and a rotating speed sensor;
the turbine comprises a single-stage or multi-stage turbine including an axial-flow turbine and a centripetal turbine, the compressor comprises a single-stage or multi-stage compressor including an axial-flow compressor and a centrifugal compressor, the generator is provided with a starting integrated generator with two working modes of a motor and a generator, the turbine, the compressor and the motor adopt a coaxial configuration mode, the heat regenerator comprises a gas-gas heat exchanger, the cooler comprises a gas-liquid heat exchanger, the bypass valve controls the opening degree through the motor drive, and the heating pipe is positioned in a pipeline used for heating a circulating working medium in the space nuclear reactor.
Preferably, the heat dissipation subsystem comprises a radiation radiator and a circulating pump;
the radiation radiator comprises a heat pipe type, fluid loop type or liquid drop type radiator, and the circulating pump is used for driving cooling liquid to complete heat exchange circulation in the cooler in the Brayton thermoelectric conversion system and the radiation radiator.
Preferably, the cycle fluid storage and supply subsystem includes: the device comprises a high-pressure gas cylinder, an electric explosion valve, an inflation electromagnetic valve, a pressure reducer, an inflation one-way valve, an air exhaust electromagnetic valve, an air extractor and an air exhaust one-way valve;
the high-pressure gas cylinder is filled with helium-xenon mixed gas, and the air extractor comprises a centrifugal compressor or a positive displacement compressor.
Preferably, the reactor auxiliary heat dissipation subsystem includes: the device comprises a cooling pipeline, a helium gas bottle, a helium electric explosion valve, a helium electromagnetic valve, a helium gas compressor and a gas radiator;
helium in the helium gas cylinder is used for the coolant of the reactor auxiliary heat dissipation subsystem, the helium gas compressor comprises a centrifugal compressor or a positive displacement compressor, and the gas radiator comprises a helium radiation radiator.
Preferably, the electric propulsion subsystem comprises: a xenon gas cylinder and an electric thruster;
the electric thruster is a high-voltage direct-drive electric thruster.
Preferably, the electrical load subsystem includes: a voltage converter and a load module;
the voltage converter converts the high voltage at the generator end into the voltage required by the load.
Compared with the prior art, the invention has the following beneficial effects:
1) the helium-xenon mixed gas is used as a circulating working medium, the closed Brayton cycle is adopted for thermoelectric conversion, the conversion efficiency is more than 30%, and the efficient conversion from nuclear energy to electric energy and power is realized;
2) the high-voltage direct-drive electric propulsion system directly utilizes high-power high-voltage electric energy generated by the thermoelectric conversion system to drive the electric thruster, a power supply processing unit is omitted, the weight and the structural complexity of the electric propulsion system are reduced, and meanwhile, the electric thruster has high specific impulse which is not less than 7000s and high thrust of 40N;
3) the power regulation mode with different response speeds of bypass regulation and air extraction regulation is provided, and the energy and power requirements of different tasks of the aircraft are met.
The invention is suitable for aircrafts which run on the rail for a long time by taking nuclear energy as power, and particularly has obvious application advantages in the aspects of deep space exploration, space tug, near-ground track cleaning and the like.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic structural diagram of a closed brayton cycle-based spatial high-power nuclear power system according to an embodiment of the present invention;
reference numerals: 1-a spatial nuclear reactor; 2-a Brayton thermoelectric conversion subsystem; 21-heating a tube; 22-a turbine; 23-a compressor; 24-a generator; 25-a heat regenerator; 26-a cooler; 27-a bypass valve; 28-a temperature sensor; 29-a pressure sensor; 210-a rotational speed sensor; 3-a heat dissipation subsystem; 31-a circulation pump; 32-a radiant cooler; 4-a circulating working medium storage and supply subsystem; 41-high pressure gas cylinder; 42-an electric explosion valve; 43-inflation solenoid valve; 44-a pressure reducer; 45-inflation check valve; 46-a suction solenoid valve; 47-air extractor; 48-air suction one-way valve; 5-reactor auxiliary cooling subsystem; 51-a cooling line; 52-helium gas cylinder; 53-helium gas electric explosion valve; 54-helium solenoid valve; 55-helium compressor; 56-gas radiator; 6-an electric propulsion subsystem; a 61-xenon gas cylinder; 62-an electric thruster; 7-an electrical load subsystem; 71-a voltage converter; 72-a load module; 81-pipeline one; 82-cable one; 83-cable two; 84-pipe two.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The first embodiment is as follows:
fig. 1 is a schematic structural diagram of a closed brayton cycle-based spatial high-power nuclear power system according to an embodiment of the present invention. As shown in fig. 1, the space high-power nuclear power system based on the closed brayton cycle provided by the invention comprises a space nuclear reactor 1, a brayton thermoelectric conversion subsystem 2, a heat dissipation subsystem 3, a circulating working medium storage and supply subsystem 4, a reactor auxiliary heat dissipation subsystem 5, an electric propulsion subsystem 6 and an electric load subsystem 7. The temperature of a helium xenon circulating working medium of the Brayton thermoelectric conversion subsystem 2 is increased by the space nuclear reactor 1 through the internal heating pipe 21, the turbine 22 in the Brayton thermoelectric conversion subsystem 2 converts the heat energy of the high-temperature high-pressure circulating working medium into shaft power, part of the shaft power is used for driving the compressor 23 to complete working medium circulating pressurization, and surplus shaft power drives the generator 24 to output electric energy. The Brayton thermoelectric conversion subsystem 2 is respectively connected with the circulating working medium storage and supply subsystem 4, the heat dissipation subsystem 3, the electric propulsion subsystem 6 and the electric load subsystem 7 through a pipeline I81, a pipeline II 84, a cable I82 and a cable II 83.
The space nuclear reactor 1 is a megawatt-level small space reactor, and can take helium or helium-xenon mixed gas as a heat carrier to lead out the heat in the reactor.
The Brayton thermoelectric conversion subsystem 2 comprises a heating pipe 21, a turbine 22, a compressor 23, a generator 24, a heat regenerator 25, a cooler 26, a bypass valve 27, a temperature sensor 28, a pressure sensor 29 and a rotating speed sensor 210. The turbine 22 is a single-stage or multi-stage turbine including an axial-flow turbine and a radial-flow turbine, the compressor 23 is a single-stage or multi-stage compressor including an axial-flow compressor and a centrifugal compressor, the generator 24 is a starting integrated generator having two working modes of a motor and a generator, the turbine 22, the compressor 23 and the motor 24 are coaxially arranged, the regenerator 25 is a gas-gas heat exchanger with high compactness and heat exchange efficiency, the cooler 26 is a gas-liquid heat exchanger with high compactness and heat exchange efficiency, the bypass valve 27 is a valve driven by the motor to control the opening degree, and the heating pipe 21 is a pipeline located in the space nuclear reactor 1 for heating a circulating working medium.
The heat dissipation subsystem 3 includes a circulation pump 31 and a radiator 32. The circulation pump 31 is used for driving the cooling liquid to complete heat exchange circulation in the cooler 26 and the radiation radiator 32 in the brayton thermoelectric conversion system 2, and the radiation radiator 32 is a heat pipe type, fluid loop type or liquid droplet type radiator meeting the space heat dissipation requirement.
The circulating working medium storage and supply subsystem 4 comprises: a high-pressure gas cylinder 41, an electric explosion valve 42, an inflation electromagnetic valve 43, a pressure reducer 44, an inflation one-way valve 45, an air extraction electromagnetic valve 46, an air extractor 47 and an air extraction one-way valve 48. The high-pressure gas cylinder 41 is filled with helium-xenon mixed gas, and the air pump 47 is a centrifugal compressor or a positive displacement compressor.
The reactor auxiliary heat dissipation subsystem 5 comprises: the cooling pipeline 51, a helium gas bottle 52, a helium electric explosion valve 53, a helium electromagnetic valve 54, a helium gas compressor 55 and a gas radiator 56. The cooling pipeline 51 is a pipeline for cooling the reactor in the spatial nuclear reactor 1, the helium gas in the helium gas cylinder 52 is used as a coolant for the reactor auxiliary heat dissipation system 5, the helium gas compressor 55 is a centrifugal compressor or a positive displacement compressor, and the gas radiator 56 is a helium gas radiation radiator.
Said electric propulsion subsystem 6, comprising: a xenon gas cylinder 61 and an electric thruster 62. The electric thruster 62 is a high-voltage direct-drive electric thruster.
The electrical load subsystem 7 comprises: a voltage converter 71 and a load module 72. The voltage converter 71 converts the high voltage at the generator 24 end into the voltage required by the load, and the load module 72 includes various electric devices, sensors, etc. on the aircraft.
The invention provides a space high-power nuclear power system based on closed Brayton cycle, which mainly comprises three processes of starting, working, power regulation and stopping:
the space high-power nuclear power system based on the closed Brayton cycle starts to be started after the aircraft reaches a specified altitude, and the working process of the system from starting to full power output is as follows. The electric explosion valve 42 in the circulating working medium storage subsystem 4 is detonated, the gas filling electromagnetic valve 43 is opened, the helium-xenon mixed gas in the high-pressure gas cylinder 41 passes through the pressure reducer 44 and the gas filling one-way valve 45 and enters the Brayton thermoelectric conversion subsystem 2 through the pipeline I81, and the bypass valve 27 is in a closed state at the moment. When the pressure sensor 29 detects that the pressure reaches the set value, the inflation solenoid valve 43 is closed, and the inflation is stopped. The helium electric explosion valve 53 is initiated, the helium electromagnetic valve 54 is opened, the space nuclear reactor 1 is started, the helium compressor 55 is started, the helium radiates heat for the reactor through the cooling pipeline 51, and the heat is discharged to the space environment through the helium radiator 56. After the temperature of the spatial nuclear reactor 1 gradually rises to a set value, the generator 24 is started, the generator 24 is in a motor mode at the moment, the turbine 22 and the compressor 23 are driven to rotate, the helium-xenon circulating working medium in the Brayton thermoelectric conversion subsystem 2 starts to circulate, and the working medium enters the turbine 22 to do work through expansion after absorbing heat through the heating pipe 21 in the spatial nuclear reactor 1. Meanwhile, the circulation pump 31 in the heat dissipation subsystem 3 is started, and the cooling liquid enters the cooler 26 through the second pipe 84 under the driving of the circulation pump 31, and then the waste heat of the brayton thermoelectric conversion subsystem 2 is discharged to the space environment through the radiation radiator 32. The temperature of the spatial nuclear reactor 1 is continuously raised, the output power of the turbine 22 is gradually increased, and when the output power of the turbine 22 is larger than the power consumed by the compressor 23, the generator 24 enters a power generation mode. The temperature of the space nuclear reactor 1 is continuously raised, the output power of the turbine 22 reaches a full load state, at the moment, the output electric power of the generator 24 reaches a rated value, the helium gas compressor 55 in the reactor auxiliary heat dissipation subsystem 5 is closed, and the reactor auxiliary heat dissipation subsystem 5 stops working.
In the working process of the space high-power nuclear power system based on the closed Brayton cycle after the starting is completed, the high-voltage electric energy output by the generator 24 has two using modes, firstly, the high-voltage electric energy is transmitted to the electric thruster 62 in the electric propulsion subsystem 6 through the first cable 82, and at the moment, the xenon gas cylinder 61 simultaneously supplies xenon working medium to the electric thruster 62, so that the nuclear power propulsion is realized; and the second is transmitted to the electric load subsystem 7 through a second cable 83, and is subjected to voltage reduction through the voltage converter 71 and then is supplied to the load module 72 for use. At the same time, the system may adjust the output electric power according to the real-time electric power demand of the electric propulsion subsystem 6 or the electric load subsystem 7. The power regulation mode includes both bypass regulation and bleed regulation. In the bypass adjusting mode, in the full-power working process of the system, the bypass valve 27 in the Brayton thermoelectric conversion subsystem 2 is opened, the flow of bypass gas is adjusted by controlling the opening degree of the bypass valve, at this time, part of high-pressure helium and xenon gas at the outlet of the compressor 23 does not pass through the turbine 22 to do work and is directly mixed with helium and xenon gas at the outlet of the turbine 22, so that the power of the output shaft of the turbine 22 is reduced, and the bypass adjusting mode can quickly adjust the output electric power of the system. In the air-bleeding adjusting mode, the bypass valve 27 is kept closed, the air-bleeding electromagnetic valve 46 and the air-bleeding compressor 45 are opened, the circulating working medium in the Brayton thermoelectric conversion system 2 returns to the high-pressure gas cylinder 41 through the first pipeline 81 through the air-bleeding electromagnetic valve 46, the air-bleeding compressor 45, the air-bleeding one-way valve 48 and the electric explosion valve 42, and the output electric power of the system is changed by changing the mass flow of the helium-xenon circulating working medium in the Brayton thermoelectric conversion subsystem 2. The bleed air regulation mode is slower in response speed than the bypass regulation, but can maintain a relatively high conversion efficiency at low loads.
The shutdown process of the space high-power nuclear power system based on the closed Brayton cycle is as follows. The power of the space reactor 1 is gradually reduced, the air exhaust electromagnetic valve 46 and the air exhaust compressor 45 are opened, the circulating working medium in the Brayton thermoelectric conversion subsystem 2 returns to the high-pressure gas cylinder 41 through the first pipeline 81 and the air exhaust electromagnetic valve 46, the air exhaust compressor 45, the air exhaust one-way valve 48 and the electric explosion valve 42, and the rotating speed of the motor 24 is gradually reduced to a set rotating speed and then enters a motor mode to stop outputting electric energy. A helium solenoid valve 54 in the reactor auxiliary heat dissipation system 5 is opened and a helium compressor 55 is started, helium dissipates heat for the reactor through a cooling pipeline 51, and heat is discharged to the space environment through a helium radiator 56. And (3) turning off the motor 24, stopping the turbine 22 and the compressor 23 from rotating, continuously operating the reactor auxiliary heat dissipation system 5, and turning off the helium compressor 55 when the temperature of the spatial nuclear reactor 1 is reduced to a set value. The shutdown process is complete.
The high-power space nuclear power system based on the closed Brayton cycle provided by the embodiment has the following advantages:
1) the helium-xenon mixed gas is used as a circulating working medium, the closed Brayton cycle is adopted for thermoelectric conversion, the conversion efficiency is more than 30%, and the efficient conversion from nuclear energy to electric energy and power is realized;
2) the high-voltage direct-drive electric propulsion system directly utilizes high-power high-voltage electric energy generated by the thermoelectric conversion system to drive the electric thruster, a power supply processing unit is omitted, the weight and the structural complexity of the electric propulsion system are reduced, and meanwhile, the electric thruster has high specific impulse which is not less than 7000s and high thrust of 40N;
3) the power regulation mode with different response speeds of bypass regulation and air extraction regulation is provided, and the energy and power requirements of different tasks of the aircraft are met.
The invention is suitable for aircrafts which run on the rail for a long time by taking nuclear energy as power, and particularly has obvious application advantages in the aspects of deep space exploration, space tug, near-ground track cleaning and the like.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (6)
1. A space high-power nuclear power system based on closed Brayton cycle is characterized by comprising: the system comprises a space nuclear reactor, a Brayton thermoelectric conversion subsystem, a heat dissipation subsystem, a circulating working medium storage and supply subsystem, a reactor auxiliary heat dissipation subsystem, an electric propulsion subsystem and an electric load subsystem;
the temperature of a circulating working medium of the Brayton thermoelectric conversion subsystem is increased by the space nuclear reactor through an internal heating pipeline, a turbine in the thermoelectric conversion subsystem converts the heat energy of the high-temperature and high-pressure circulating working medium into shaft power, part of the shaft power is used for driving a gas compressor to complete the circulating pressurization of the working medium, and surplus shaft power drives a generator to output electric energy; the Brayton thermoelectric conversion subsystem is respectively connected with the heat dissipation subsystem, the circulating working medium storage and supply subsystem, the electric propulsion subsystem and the electric load subsystem through a pipeline I, a pipeline II, a cable I and a cable II;
the space nuclear reactor is a megawatt-level small space reactor, and helium or helium-xenon mixed gas is used as a heat carrying agent to lead out heat inside the reactor;
the Brayton thermoelectric conversion subsystem adopts helium-xenon mixed gas as a circulating working medium and comprises a heating pipe, a turbine, a gas compressor, a generator, a heat regenerator, a cooler, a bypass valve, a temperature sensor, a pressure sensor and a rotating speed sensor;
the turbine comprises a single-stage or multi-stage turbine including an axial-flow turbine and a centripetal turbine, the compressor comprises a single-stage or multi-stage compressor including an axial-flow compressor and a centrifugal compressor, the generator is provided with a starting integrated generator with two working modes of a motor and a generator, the turbine, the compressor and the motor adopt a coaxial configuration mode, the heat regenerator comprises a gas-gas heat exchanger, the cooler comprises a gas-liquid heat exchanger, the bypass valve controls the opening degree through the motor drive, and the heating pipe is positioned in a pipeline used for heating a circulating working medium in the space nuclear reactor.
2. The closed brayton cycle-based space high-power nuclear power system of claim 1, wherein the heat rejection subsystem comprises a radiation radiator and a circulation pump;
the radiation radiator comprises a heat pipe type, fluid loop type or liquid drop type radiator, and the circulating pump is used for driving cooling liquid to complete heat exchange circulation in the cooler in the Brayton thermoelectric conversion system and the radiation radiator.
3. The closed Brayton cycle-based spatial high-power nuclear power system according to claim 1, wherein the cycle fluid storage and supply subsystem comprises: the device comprises a high-pressure gas cylinder, an electric explosion valve, an inflation electromagnetic valve, a pressure reducer, an inflation one-way valve, an air exhaust electromagnetic valve, an air extractor and an air exhaust one-way valve;
the high-pressure gas cylinder is filled with helium-xenon mixed gas, and the air extractor comprises a centrifugal compressor or a positive displacement compressor.
4. The closed brayton cycle-based space high-power nuclear power system of claim 1, wherein the reactor auxiliary heat dissipation subsystem comprises: the device comprises a cooling pipeline, a helium gas bottle, a helium electric explosion valve, a helium electromagnetic valve, a helium gas compressor and a gas radiator;
helium in the helium gas cylinder is used for the coolant of the reactor auxiliary heat dissipation subsystem, the helium gas compressor comprises a centrifugal compressor or a positive displacement compressor, and the gas radiator comprises a helium radiation radiator.
5. The closed brayton cycle-based space high-power nuclear power system of claim 1, wherein said electric propulsion subsystem comprises: a xenon gas cylinder and an electric thruster;
the electric thruster is a high-voltage direct-drive electric thruster.
6. The closed brayton cycle-based space high-power nuclear power system according to claim 1, wherein said electrical load subsystem comprises: a voltage converter and a load module;
the voltage converter converts the high voltage at the generator end into the voltage required by the load.
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| CN115014784A (en) * | 2022-06-17 | 2022-09-06 | 中国核电工程有限公司 | Closed Brayton cycle performance experiment system |
| CN115234330A (en) * | 2022-08-30 | 2022-10-25 | 西安热工研究院有限公司 | Efficient and safe space nuclear power supply system and working method thereof |
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