CN116928903B - Heat dissipation subsystem and space nuclear energy brayton power generation system - Google Patents
Heat dissipation subsystem and space nuclear energy brayton power generation systemInfo
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- CN116928903B CN116928903B CN202310696720.5A CN202310696720A CN116928903B CN 116928903 B CN116928903 B CN 116928903B CN 202310696720 A CN202310696720 A CN 202310696720A CN 116928903 B CN116928903 B CN 116928903B
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- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21C—NUCLEAR REACTORS
- G21C15/00—Cooling arrangements within the pressure vessel containing the core; Selection of specific coolants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B30/00—Heat pumps
- F25B30/02—Heat pumps of the compression type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B9/00—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point
- F25B9/002—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point characterised by the refrigerant
- F25B9/008—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point characterised by the refrigerant the refrigerant being carbon dioxide
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- Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
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Abstract
散热子系统和空间核能布雷顿发电系统，为解决现有技术中存在的，现有的空间核能系统为降低航天成本，获得较高的星表能源系统紧凑度，往往采用较高的冷却器温度来排出废热，但较高的冷却器温度使得系统的最高输出比功降低的问题，本发明提供的技术方案为：散热子系统，应用于星表核能系统，所述子系统包括：热泵压缩机、换热器、散热器和降温器；所述换热器用于将星表核能系统中的热量通过所述热泵压缩机传递至所述散热器，所述热量经过所述散热器后，经过所述降温器降温，然后被传递至所述换热器。适合应用于空间发电系统的搭建和研究工作中。
The heat dissipation subsystem and space nuclear Brayton power generation system address the existing technical problem that existing space nuclear energy systems often use higher cooler temperatures to dissipate waste heat to reduce spaceflight costs and achieve a more compact surface energy system. However, this higher cooler temperature reduces the system's maximum output specific work. The present invention provides a technical solution: a heat dissipation subsystem, applied to a surface nuclear energy system, comprising a heat pump compressor, a heat exchanger, a radiator, and a cooler. The heat exchanger is used to transfer heat from the surface nuclear energy system to the radiator via the heat pump compressor. After passing through the radiator, the heat is cooled by the cooler before being transferred to the heat exchanger. This solution is suitable for use in the construction and research of space power generation systems.
Description
Technical Field
Relates to the field of space nuclear power, in particular to space nuclear power generation.
Background
With the development of deep space exploration, the design of an energy system of a star warhead resident base is highly interesting for aerospace researchers in various countries. Taking a lunar base as an example, the lunar surface resident base needs to meet the technical requirements of high energy density, high reliability, long service life and the like. In addition, in consideration of high emission and transportation costs of aerospace tasks, the designed base energy system meets the technical requirements, and simultaneously has the lowest possible weight cost, the lowest possible operation cost and the highest possible equipment compactness. The space nuclear energy system has the characteristics of high energy density, strong stability and long service life, so that the nuclear energy has a very high application prospect on the star-surface-base energy system. According to the technical characteristics of thermoelectric conversion, the conversion modes can be divided into static conversion and dynamic conversion according to the existence of a working element. The lower energy conversion rate has led to a continued search for applications that are powered at the base due to the technical limitations of static conversion. The dynamic conversion comprises Rankine cycle, brayton cycle and Stirling cycle, and the conversion efficiency is high and can reach more than 20%, so that considerable advantages are presented in the design of the energy system of the star table base with harsh conditions.
Since the alkali metal rankine cycle has the problem of an alkali metal two-phase flow, there is a certain safety risk during operation, and therefore, further investigation is required in the application of weak gravitational fields. The Stirling cycle is difficult to output at high power due to its inherent structural characteristics, and therefore requires further optimization in the application of the star energy system. The brayton cycle has high thermal efficiency, and has no technical characteristics of unstable two-phase flow and the like, so that the brayton cycle has considerable application prospect in star energy base application with larger energy demand. In a conventional spatial brayton cycle, a nuclear reactor, a turbine, a radiant cooler, and a compressor are included.
Unlike the ground brayton system, waste heat of the space brayton system is removed via a radiant radiator. The heat exchange capacity per unit radiation in space is as follows:
Where ε is the emissivity of the material, σ is the emissivity constant, T 1 is the radiant panel temperature, and T 0 is the space temperature. In space, especially on a star chart without atmosphere, the space temperature is considered to be a constant value of 4K.
From the above equation, it can be derived that the waste heat removal capacity of spatial brayton is positively correlated with the radiant panel temperature. The higher the temperature of the radiant panel, the stronger the waste heat removal capability. Under the condition of a certain total amount of waste heat, the higher the temperature of the radiation heat dissipation plate is, the smaller the required heat exchange area is. The temperature of the radiant radiator can also affect the thermal performance of the spatial brayton system. Taking helium xenon working medium with pressure below 2Mpa as an example under the condition of a constant heat source, the system output specific work is obtained under the following design working conditions:
Where pi is the turbo ratio and τ is the cyclic ratio. It can be seen from the above two formulas that the lower the temperature of the brayton cycle cooler, the higher the specific work output of the system. However, in order to reduce the space cost of the existing space nuclear energy system and obtain higher compactness of the star-meter energy system, the waste heat is often discharged by adopting a higher cooler temperature, but the highest output specific work of the system is reduced by adopting the higher cooler temperature.
Disclosure of Invention
In order to solve the problems in the prior art that the prior space nuclear energy system is used for reducing the space cost and obtaining higher compactness of the star energy system, the waste heat is usually discharged by adopting higher cooler temperature, but the highest output specific work of the system is reduced by the higher cooler temperature, the invention provides the following technical scheme:
A heat dissipation subsystem for use in a star-meter nuclear power system, the subsystem comprising:
The heat pump compressor, the heat exchanger, the radiator and the cooler;
The heat exchanger is used for transferring heat in the star-meter nuclear energy system to the radiator through the heat pump compressor, and the heat is cooled through the cooler after passing through the radiator and then transferred to the heat exchanger.
Further, a preferred embodiment is provided, wherein the heat sink is a radiant heat sink.
Further, there is provided a preferred embodiment wherein the radiant heat sink is a heat pipe radiant heat sink.
Further, a preferred embodiment is provided, wherein the radiant heat sink is a droplet radiant heat sink.
Further, there is provided a preferred embodiment wherein the desuperheater is a heat pump turbine.
Further, there is provided a preferred embodiment wherein the working medium for transferring heat is helium xenon, supercritical carbon dioxide or helium.
Further, there is provided a preferred embodiment, wherein the temperature reducer is a throttle valve.
Further, a preferred embodiment is provided, characterized in that in the system the working medium for transferring heat is benzene, ethane or water.
Based on the same inventive concept, the invention also provides a spatial nuclear brayton power generation system,
The system comprises a heat dissipation subsystem and a brayton thermoelectric conversion subsystem;
the brayton thermoelectric conversion subsystem is used for exchanging waste heat generated by a space nuclear reactor;
The heat dissipation subsystem is used for discharging the waste heat;
the heat pump compressor is coaxial with the brayton compressor and the brayton turbine in the brayton thermoelectric conversion subsystem for driving the generator.
Further, there is provided a preferred embodiment wherein the heat sink is a heat pump turbine coaxial with the heat pump compressor and adapted to drive a generator.
Compared with the prior art, the technical scheme provided by the invention has the following advantages:
According to the space nuclear energy Brayton power generation system, the nuclear energy Brayton thermoelectric conversion system and the heat pump circulation heat dissipation subsystem are coupled to form the multi-machine integrated space nuclear energy Brayton power generation system, low-temperature waste heat of the nuclear energy Brayton thermoelectric conversion system is transported to the radiation radiator by the heat pump system, the radiation area of the radiation radiator is reduced, the specific mass output work of the space nuclear energy Brayton power generation system is improved, and the compactness of the star meter nuclear energy Brayton system is improved;
The invention provides a space nuclear energy Brayton power generation system, which provides two different types of heat pump systems, namely a heat pump heat dissipation system based on a reverse Brayton cycle and a heat pump heat dissipation system based on a reverse Rankine cycle, wherein the heat pump heat dissipation systems can be flexibly selected according to different aerospace requirements;
The spatial nuclear energy Brayton power generation system provided by the invention has strong expandability, and the function realization of the multi-machine integrated spatial nuclear energy Brayton power generation system is independent of the selection of working media of each subsystem, so that the system can be designed by combining the resource characteristics of different star meters, and has wide application and development prospects in space tasks.
The space nuclear energy Brayton power generation system overcomes the defects in the space nuclear energy Brayton system technology, provides a design scheme capable of guaranteeing a smaller heat dissipation area of the space nuclear energy Brayton system and improving the output specific function of an energy system, and solves the contradiction between the work requirement of the space nuclear energy Brayton system and the heat dissipation area of the system to a certain extent by introducing the reverse thermodynamic cycle of a heat pump, thereby realizing the star nuclear energy system design with high compactness.
The method is suitable for being applied to the construction and research work of a space power generation system.
Drawings
FIG. 1 is a system schematic diagram of a spatial nuclear Brayton power generation system according to embodiment nine;
fig. 2 is a system schematic diagram of a spatial nuclear brayton power generation system according to a ninth embodiment.
Wherein 1-8 are state nodes, 9 are space nuclear reactors, 10 are heaters, 11 are brayton compressors, 12 are brayton turbines, 13 are heat exchangers, 14 are heat pump compressors, 15 are radiant radiators, 16 are heat pump turbines, 17 are throttle valves, 18 are spindles, 19 are gearboxes, and 20 are generators.
Detailed Description
In order to make the advantages and benefits of the technical solution provided by the present invention more apparent, the technical solution provided by the present invention will now be described in further detail with reference to the accompanying drawings, in which:
in a first embodiment, a heat dissipation subsystem is provided and applied to a star-meter nuclear energy system, where the subsystem includes:
a heat pump compressor 14, a heat exchanger 13, a radiator and a desuperheater;
The heat exchanger 13 is used for transferring heat in the star-meter nuclear energy system to the radiator through the heat pump compressor 14, and after passing through the radiator, the heat is cooled by the cooler and then transferred to the heat exchanger 13.
The second embodiment and the present embodiment are further defined as the heat dissipation subsystem provided in the first embodiment, and the heat sink is a radiation heat sink 15.
The third embodiment and the present embodiment are further defined on the heat dissipation subsystem provided in the second embodiment, and the radiation radiator 15 is a heat pipe radiation radiator.
The fourth embodiment and the present embodiment are further defined on the heat dissipation subsystem provided in the second embodiment, and the radiation heat sink 15 is a droplet radiation heat sink.
The fifth embodiment is a further limitation of the heat dissipation subsystem provided in the first embodiment, and the cooler is a heat pump turbine 16.
In a sixth embodiment, the present embodiment is a further limitation of the heat dissipation subsystem provided in the fifth embodiment, where the working medium for transferring heat is helium xenon, supercritical carbon dioxide or helium.
Embodiment seven and this embodiment are further defined on the heat dissipation subsystem provided in the first embodiment, and the temperature reducer is a throttle valve 17.
Embodiment eight and this embodiment are further limitations on the heat dissipation subsystem provided in embodiment seven, where the working medium used for transferring heat is benzene, ethane or water.
Embodiment nine, described in connection with fig. 1 and 2, this embodiment provides a spatial nuclear brayton power generation system,
The system comprises a heat dissipation subsystem and a brayton thermoelectric conversion subsystem;
the brayton thermoelectric conversion subsystem is used for exchanging waste heat generated by the space nuclear reactor 9;
The heat dissipation subsystem is provided in the first embodiment, and is used for discharging the waste heat;
The heat pump compressor 14 is coaxial with the brayton compressor 11 and brayton turbine 12 in the brayton thermoelectric conversion subsystem for driving the generator 20.
Specific:
The implementation mode is realized by the following technical scheme:
with reference to fig. 1 and 2.
The system comprises a nuclear energy Brayton thermoelectric conversion subsystem and a heat pump circulation heat dissipation subsystem, namely a heat dissipation subsystem;
the brayton thermoelectric conversion subsystem comprises a space nuclear reactor 9, a brayton turbine 12, a heat exchanger 13, a brayton compressor 11, pipelines for connecting the components, and the like.
According to the prior researches, the working medium of the brayton thermoelectric conversion subsystem can be helium-xenon mixed gas, supercritical carbon dioxide, other working mediums suitable for the spatial brayton thermoelectric system and the like. In the Brayton thermoelectric conversion system, a high-pressure working medium is heated by a nuclear reactor at constant pressure to reach a state point 1, the high-temperature and high-pressure working medium is subjected to medium entropy expansion in a Brayton turbine 12 to achieve a low-pressure and medium-temperature state point 2, the low-pressure and medium-temperature working medium is subjected to constant pressure to remove waste heat in a heat exchanger 13 to achieve a low-temperature and low-pressure state point 3, the low-temperature and low-pressure working medium enters a Brayton compressor 11 to be compressed to enter a medium-temperature and high-pressure state point 4, and the working medium in the medium-temperature and high-pressure state is heated by the nuclear reactor at constant pressure to reach the state point 1 and complete a thermodynamic cycle.
The heat pump cycle heat dissipation subsystem comprises two types, namely a heat pump heat dissipation system based on a reverse brayton cycle in fig. 1 and a heat pump heat dissipation system based on a reverse rankine cycle in fig. 2.
The heat pump heat dissipation system based on the reverse brayton cycle is shown in fig. 1. This type of subsystem consists of a heat exchanger 13, a heat pump compressor 14, a radiant radiator 15, a heat pump turbine 16 and pipes connecting the components.
The radiant heat exchanger 13 depicted in fig. 1 may be a heat pipe radiator or a droplet radiant heat radiator 15.
The working medium of the heat pump cycle subsystem (reverse brayton) in fig. 1 may be helium xenon, supercritical carbon dioxide, helium, and other working mediums suitable for use in reverse brayton thermodynamic systems, and the like. In the system, a working medium in a low-temperature low-pressure state absorbs waste heat discharged by a Brayton thermoelectric conversion subsystem at a constant pressure in a heat exchanger 13 to reach a state point 5, the working medium with heat absorption and temperature rise is compressed in a heat pump compressor 14 in an adiabatic manner to reach a state point 6, the working medium with high temperature and high pressure discharges heat to the outer space through a radiation radiator 15 to reach a state point 7, the cooled working medium with high pressure is discharged into a heat pump turbine 16 to expand and do work to reach a state point 8, and the working medium with low temperature and low pressure absorbs heat in the heat exchanger 13 again to reach the state point 5 to complete a cycle.
In the spatial nuclear brayton power generation system consisting of the nuclear brayton thermoelectric conversion subsystem and the heat pump cycle heat dissipation subsystem (inverse brayton), the brayton compressor 11, brayton turbine 12, heat pump compressor 14, heat pump turbine 16 and generator 20 are integrated into a set of rotating shafts by a set of gearboxes 19, and power is supplied to the external system.
The heat pump heat dissipation system based on the reverse rankine cycle is shown in fig. 2. This type of subsystem consists of a heat exchanger 13, a heat pump compressor 14, a radiant radiator 15, a throttle valve 17 and pipes connecting the components.
The radiant heat exchanger 13 depicted in fig. 2 may be a heat pipe radiator or a droplet radiant heat radiator 15.
The working medium of the heat pump circulation subsystem (inverse Rankine) in FIG. 2 can be benzene, ethane, water, other working media suitable for inverse Rankine thermodynamic systems, and the like. In the system, a low-temperature low-pressure wet saturated steam working medium absorbs waste heat discharged by a Brayton thermoelectric conversion subsystem in a heat exchanger 13 at constant pressure to reach a saturated state 5, a dry saturated working medium is compressed in a heat pump compressor 14 in an adiabatic manner to reach an overheat state point 6, high-temperature high-pressure overheat working medium steam discharges heat to the outer space through constant pressure of a radiation radiator 15 and finally reaches a saturated liquid phase state 7 under corresponding pressure at an outlet of the radiation radiator 15, the saturated liquid phase working medium enters a throttle valve 17 and is cooled and depressurized to a wet saturated steam state 8, and the low-temperature low-pressure wet saturated steam working medium absorbs heat in the heat exchanger 13 to reach the state point 5 to complete one cycle.
In the spatial nuclear brayton power generation system consisting of the nuclear brayton thermoelectric conversion subsystem and the heat pump cycle heat dissipation subsystem (inverse rankine), the brayton compressor 11, brayton turbine 12, heat pump compressor 14 and generator 20 are integrated into a set of main shafts 18 by a set of gearboxes 19, and power is supplied to the external system.
Embodiment ten and this embodiment are further limitations on the space nuclear brayton power generation system provided in embodiment nine, wherein in the heat dissipation subsystem, the temperature reducer is a heat pump turbine 16, and the heat pump turbine 16 is coaxial with the heat pump compressor 14 and is used for driving the generator 20.
An eleventh embodiment is a specific implementation manner provided for the spatial nuclear energy brayton power generation system provided in the ninth embodiment, specifically:
the key design parameters of the system are shown in the following table:
Table 1 key parameters of multi-machine integrated space nuclear energy Brayton power generation system
In table 1, τ is the system warming ratio, and the obtained expression is:
Wherein T 3 is the outlet temperature of the nuclear energy Brayton thermoelectric conversion subsystem heat exchanger 13 of FIGS. 1 and 2. Kappa is the adiabatic index of the working fluid in Table 1, which is 1.678 in this example.
The embodiment adopts a reverse brayton heat pump heat radiation system taking helium xenon as a working medium to be coupled with a nuclear brayton thermoelectric conversion subsystem. In this embodiment, the system iterative design is performed by using the technical route that the inlet temperature of the heat pump radiator is not coupled and the inlet temperature of the radiation heat exchanger 13 is 600K, the inlet temperature of the cold side of the heat exchanger 13 is 300K, and the inlet temperature of the heat pump radiator is coupled and the inlet temperature of the cold side of the heat exchanger 13 is 300K, and the inlet temperature of the radiation heat exchanger 15 is 600K.
Table 2 shows system design parameters for a heat pump radiator not coupled and a cold side inlet temperature of 300K for heat exchanger 13.
Table 2 Star-table nuclear energy system parameters of 300K inlet temperature at the cold side of heat exchanger 13 without coupling heat pump radiator
In the design scheme of the system, helium xenon with the pressure of 1.5Mpa is heated to 1300K by a nuclear reactor, high-temperature high-pressure helium xenon enters a Brayton turbine 12 to expand and do work, the temperature of the high-temperature high-pressure helium xenon is reduced to 663.5K, the pressure of the high-temperature high-pressure helium xenon is reduced to 0.282Mpa, working medium subjected to work is subjected to waste heat removal through a heat exchanger 13, the temperature of the working medium is further reduced to 336.4K, the low-temperature low-pressure helium xenon is compressed through a Brayton compressor 11, the pressure of the low-temperature low-pressure helium xenon is increased to 1.5Mpa, the temperature of the low-temperature helium xenon is increased to 657.2K, the high-temperature low-temperature helium xenon is heated through a nuclear reactor heater 10, and the temperature of the high-pressure low-temperature helium xenon is increased to 1300K, so that a work cycle is completed. In this design, the thermal efficiency of the Stark nuclear Brayton system is 43.9% and the specific work cycle is 148.58kJ/kg. The required heat dissipation area of the system radiation heat sink 15 is 2200m 2.
Table 3 shows the system design parameters for a radiant heat exchanger 13 inlet temperature of 600K without coupling the heat pump radiator.
Table 3 star-meter nuclear energy system parameters with a 600K inlet temperature of radiant heat exchanger 13 without coupling heat pump radiator
In the design scheme of the system, helium xenon with the pressure of 1.5Mpa is heated to 1300K by a nuclear reactor, high-temperature high-pressure helium xenon enters a Brayton turbine 12 to expand and do work, the temperature of the high-temperature high-pressure helium xenon is reduced to 908.6K, the pressure of the high-temperature high-pressure helium xenon is reduced to 0.612Mpa, working medium subjected to work is subjected to waste heat removal through a heat exchanger 13, the temperature of the working medium is further reduced to 630.8K, the low-temperature low-pressure helium xenon is compressed through a Brayton compressor 11, the pressure of the low-temperature low-pressure helium xenon is increased to 1.5Mpa, the temperature of the low-temperature helium xenon is increased to 904.1K, the high-temperature low-temperature helium xenon is heated through a nuclear reactor heater 10, and the temperature of the high-pressure low-temperature helium xenon is increased to 1300K, so that a work cycle is completed. In this design, the thermal efficiency of the Stark nuclear Brayton system is 23.7% and the specific work cycle is 48.56kJ/kg. The required heat dissipation area of the system radiant heat sink 15 is 193m 2.
Table 4 shows the system design parameters for a coupled heat pump radiator with a 300K cold side inlet temperature of the heat exchanger 13 and a 600K inlet temperature of the radiant radiator 15.
TABLE 4 Table 4
In the system design scheme, in terms of a Brayton thermoelectric conversion subsystem, helium xenon with the pressure of 1.5Mpa is heated to 1300K by a nuclear reactor, high-temperature high-pressure helium xenon enters the Brayton turbine 12 to expand and do work, the temperature of the high-temperature high-pressure helium xenon is reduced to 663.5K, the pressure of the high-temperature high-pressure helium xenon is reduced to 0.282Mpa, waste heat is discharged by a heat exchanger 13 after working, the temperature of the working medium subjected to work is further reduced to 336.4K, the low-temperature low-pressure helium xenon is compressed by the Brayton compressor 11, the pressure of the low-pressure helium xenon is increased to 1.5Mpa, the temperature of the low-pressure helium xenon is increased to 657.2K, the high-pressure low-temperature helium xenon is heated by the nuclear reactor heater 10, the temperature of the high-pressure low-temperature helium xenon is increased to 1300K, and a work cycle is completed. In the aspect of a heat pump circulation heat dissipation subsystem, helium xenon with the pressure of 0.3Mpa and the temperature of 300K is heated to 426K by a heat exchanger 13, helium xenon with medium temperature and low pressure enters a heat pump compressor 14 for compression, the temperature of the helium xenon is increased to 600K, the pressure of the helium xenon is increased to 1.08Mpa, high-temperature and high-pressure helium xenon passes through a radiation radiator 15 to remove waste heat, the temperature of the helium xenon is further reduced to 450K, the helium xenon with medium temperature and high pressure does work by a heat pump turbine 16, the pressure of the helium xenon is reduced to 0.3Mpa, the temperature of the helium xenon is reduced to 300K, and the helium xenon with low temperature and low pressure enters the heat exchanger 13 for heating, so that a heat transport cycle is completed. In this design, the thermal efficiency of the Stark nuclear Brayton system is 25.4% and the specific work cycle is 84.2kJ/kg. The required heat dissipation area of the system radiant heat sink 15 is 200m 2.
In summary, in this embodiment, under the condition that the inlet temperature of the cold side of the heat exchanger 13 is 300K, the thermal efficiency of the coupled heat pump heat dissipation star nuclear energy system is 56% of the thermal efficiency of the uncoupled heat pump nuclear energy system, the specific power of the system is 57% of the specific power of the uncoupled heat pump nuclear energy system, but the required heat dissipation area only occupies 9% of the uncoupled heat pump nuclear energy system, which is 200m 2. Under the condition that the inlet temperature of the radiation radiator 15 is 600K, the heat dissipation area of the coupled heat pump heat dissipation star table nuclear energy system is the same as that of the uncoupled heat pump nuclear energy system, but the heat efficiency of the coupled heat pump heat dissipation star table nuclear energy system is 1.08 times of that of the uncoupled heat pump nuclear energy system, and the specific power output of the coupled heat pump heat dissipation star table nuclear energy system is 1.75 times of that of the uncoupled heat pump nuclear energy system.
Therefore, the invention can effectively reduce the radiation heat dissipation area of the system under the condition that the inlet temperature of the cold side of the heat exchanger 13 is the same, and can effectively improve the heat efficiency and the working capacity of the system under the condition that the inlet temperature of the radiation heat exchanger 13 is the same.
The technical solution provided by the present invention is described in further detail through the specific embodiments in the above description with reference to the accompanying drawings, so as to highlight the advantages and benefits of the technical solution provided by the present invention, however, the above described specific embodiments are not to be taken as limiting the present invention, and any reasonable modification and improvement, reasonable combination of the embodiments, equivalent substitution, etc. based on the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A spatial nuclear Brayton power generation system, characterized in that,
The system comprises a heat dissipation subsystem and a brayton thermoelectric conversion subsystem;
the brayton thermoelectric conversion subsystem is used for exchanging waste heat generated by a space nuclear reactor;
the heat dissipation subsystem is used for discharging the waste heat;
A heat pump compressor is coaxial with the brayton compressor and the brayton turbine in the brayton thermoelectric conversion subsystem and is used for driving a generator;
the heat dissipation subsystem includes:
The heat pump compressor, the heat exchanger, the radiator and the cooler;
The heat exchanger is used for transferring heat in the star-meter nuclear energy system to the radiator through the heat pump compressor, and the heat is cooled through the cooler after passing through the radiator and then transferred to the heat exchanger;
The cooler is a heat pump turbine;
in the heat radiation subsystem, working media for transferring heat are helium xenon, supercritical carbon dioxide or helium.
2. The space nuclear brayton power generation system of claim 1, wherein in the heat rejection subsystem, the desuperheater is a heat pump turbine that is coaxial with the heat pump compressor and is used to drive a generator.
3. The spatial nuclear brayton power generation system of claim 1, wherein the heat sink is a radiant heat sink.
4. A spatial nuclear brayton power generation system in accordance with claim 3, wherein said radiant heat sink is a heat pipe radiant heat sink.
5. A spatial nuclear brayton power generation system in accordance with claim 3 wherein said radiant heat sink is a droplet radiant heat sink.
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| CN203512059U (en) * | 2013-08-12 | 2014-04-02 | 上海卫星工程研究所 | High-efficiency spacecraft thermal management system |
| CN109677639A (en) * | 2018-12-30 | 2019-04-26 | 上海空间推进研究所 | The high-power Nuclear Power System in space based on Closed Brayton Power Cycle |
| CN215170566U (en) * | 2021-04-20 | 2021-12-14 | 杭州明晟新能源科技有限公司 | Brayton heat pump circulating energy storage system |
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