CN109372591B - Surplus generating capacity utilizes system based on closed air compression circulation - Google Patents
Surplus generating capacity utilizes system based on closed air compression circulation Download PDFInfo
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- CN109372591B CN109372591B CN201811175018.XA CN201811175018A CN109372591B CN 109372591 B CN109372591 B CN 109372591B CN 201811175018 A CN201811175018 A CN 201811175018A CN 109372591 B CN109372591 B CN 109372591B
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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
- F01D15/10—Adaptations for driving, or combinations with, electric generators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B35/00—Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for
- F04B35/04—Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for the means being electric
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Abstract
The invention relates to a surplus power generation capacity utilization system based on closed air compression circulation, which mainly comprises: the airplane airborne surplus power generation capacity utilization subsystem utilizes surplus power generation capacity to drive the motor, and converts electric energy into rotary mechanical energy; the closed air compression circulation subsystem is used for converting electric energy into cold energy; the local power grid power supply storage subsystem drives the generator by utilizing shaft work output by the turbine, converts mechanical energy into electric energy, and stores the electric energy in the onboard storage battery pack through the local power grid for driving the pump motor; and the oil-immersed cold energy storage and supply subsystem comprises an oil-immersed heat exchanger, a cold accumulation oil tank and a high-power heat load device requiring cold energy, and three working modes that the high-power heat load device directly supplies cold energy from the closed air compression circulation subsystem, and the cold energy with surplus cold energy is stored in the cold accumulation oil tank and is supplied to the cold energy from the cold accumulation oil tank when the heat dissipation capacity of the high-power heat load device is insufficient are realized.
Description
Technical Field
The invention relates to a surplus power generation capacity utilization system based on closed air compression circulation.
Background
With the continuous development and progress of the aerospace field, the reasonable utilization and conversion of airborne energy becomes more and more important. Because the airplane is developing towards multi-electric/full-electric, in the design process of the airborne power grid, the supply of electric energy is often designed according to the highest peak value of the demand of airborne electric equipment of the airplane, therefore, in different flight stages, the airplane power grid has surplus generating capacity with different degrees, the surplus generating capacity is not fully utilized, so that the compensatory loss of the performance of an airplane system is increased, the flight performance of airplane fuel oil and the airplane is greatly reduced, and how to reasonably and efficiently utilize and convert the surplus generating capacity becomes a problem which is more and more concerned in the airborne energy field of the current multi-electric/full-electric airplane.
Due to the great trend of the multi-electric/full-electric aircraft, the number of airborne electronic equipment of the aircraft is continuously increased, meanwhile, the requirements for high power and small size of the airborne electronic equipment are increasingly high, the power density of the airborne electronic equipment is continuously increased, the requirement for the heat dissipation capability of an airborne environment control system is also increasingly high, the single air circulation refrigeration is far from meeting the overall design requirements of the multi-electric/full-electric aircraft, if the cold energy is insufficient, the heat cannot be dissipated in time, the temperature of a load can be rapidly increased, and the reliable, safe and efficient work of the airborne equipment can be greatly influenced.
With the continuous development of modern airplanes, the requirements on the maneuvering performance and the stealth performance of the airplanes are continuously improved, and ram air is severely restricted as a heat sink of an airplane environment control system, so that fuel oil becomes a main heat sink, and the efficient utilization of a cold accumulation oil tank becomes a main trend. However, the demand of the aircraft for cold energy is greatly different in different flight phases, and therefore, how to reasonably generate cold energy, utilize cold energy, and reasonably store cold energy also becomes an important bottleneck for research focus and development in the aviation field nowadays. Therefore, this trend makes the environmental control system of the aircraft more and more complex and the refrigeration form more and more, so that it is necessary to perform uniform thermal management in the whole aircraft range, that is, the application of the integrated environmental control/thermal management system.
Disclosure of Invention
According to one aspect of the present invention, there is provided a surplus power generation capacity utilization system based on a closed air compression cycle, comprising:
an electric motor for converting the electrical energy of the aircraft electrical network into mechanical energy,
a compressor driven by the motor to operate,
the air-air high-temperature heat exchanger is used for carrying out air-air heat exchange on the high-temperature and high-pressure air compressed by the compressor and the ram air,
the gas from the gas-gas high-temperature heat exchanger is cooled again through the expansion turbine,
the gas from the expansion turbine reaches a gas phase pipeline of the gas-liquid low-temperature heat exchanger through a connecting pipeline so as to transfer cold energy to oil liquid in a liquid phase pipeline of the gas-liquid low-temperature heat exchanger,
a generator which operates under the drive of the expansion turbine,
a storage battery set for storing the electric energy generated by the generator,
a pump motor that operates by being driven by electric power from the battery pack,
a pump which operates under the drive of a pump motor to drive oil,
a cold accumulation oil tank for holding liquid as heat sink,
the first oil-immersed heat exchanger is used for enabling the oil liquid from the pump to exchange heat with the heat sink in the cold storage oil tank,
a first oil line from the pump through the thermal load to the liquid phase line,
a second oil liquid pipeline connected to the liquid phase pipeline from the pump through the first oil-immersed heat exchanger,
a second check valve provided on the second oil line,
the second oil-immersed heat exchanger is used for enabling the oil liquid flowing through the second oil-immersed heat exchanger to exchange heat with the heat sink in the cold storage oil tank,
and the second oil-immersed heat exchanger, the third one-way valve and the thermal load are connected into an oil liquid loop through an additional oil liquid pipeline.
Drawings
Fig. 1 shows a schematic diagram of a surplus power generation capacity utilization system based on a closed air compression cycle according to an embodiment of the present invention.
Fig. 2 shows a work flow diagram of a surplus power generation capacity utilization system based on a closed air compression cycle according to an embodiment of the present invention.
Fig. 3 shows a schematic diagram of a first cold energy utilization mode of the closed air compression cycle based surplus power generation capacity utilization system according to an embodiment of the present invention.
Fig. 4 shows a schematic diagram of a second cold energy utilization mode of the closed air compression cycle based surplus power generation capacity utilization system according to an embodiment of the present invention.
Fig. 5 shows a schematic diagram of a third cold energy utilization mode of the surplus power generation capacity utilization system based on the closed air compression cycle according to an embodiment of the present invention.
Description of reference numerals:
101-aircraft power grid, 102-basic electric load, 103-motor, 201-compressor, 202-gas high-temperature heat exchanger, 203-expansion turbine, 204-gas-liquid low-temperature heat exchanger, 205-gas-phase heat exchanger pipeline, 301-generator, 302-local power grid, 303-storage battery pack, 401-liquid-phase heat exchanger pipeline, 402-pump, 403-pump motor, 404-first check valve, 405-high-power heat load, 406-second check valve, 407-first oil-immersed heat exchanger, 408-cold storage oil tank, 409-second oil-immersed heat exchanger, 410-third check valve.
Detailed Description
The invention provides a surplus power generation capacity utilization system based on closed air compression circulation.
The objects of the present invention include: aiming at the problems that the surplus power generation capacity of a multi-electric/full-electric aircraft developed at present is not fully utilized and the onboard cold energy is not stored, utilized and supplied enough, a surplus power generation capacity utilization system based on closed air compression circulation is provided, so that the onboard surplus power generation capacity of the multi-electric/full-electric aircraft can be fully utilized, the energy dispatching is realized, the abundant cold energy is provided for storage and utilization, the self-regulation capacity of a high-power heat load heat dissipation system is provided, the use requirement of a refrigeration system on ram air is reduced, and the low compensation loss of the aircraft cooling requirement is realized.
The invention utilizes the surplus power generation capacity of the airplane power grid to drive the closed compressed air circulating system to convert electric energy into cold energy, on one hand, the cold energy is directly supplied to the airplane airborne high-power heat load for heat dissipation and cooling, and on the other hand, the surplus cold energy is carried and conveyed by Poly Alpha Olefin (PAO) oil liquid to be stored in the fuel oil heat sink of the cold storage oil tank so as to supply cold energy under the condition of insufficient supply of the high-power heat load cold energy.
The surplus power utilization system based on the closed air compression cycle according to one embodiment of the invention is shown in fig. 1 and comprises an aircraft onboard surplus power utilization subsystem, a closed air compression cycle subsystem, a local power grid power supply storage subsystem and an oil-immersed cold energy storage and supply subsystem. The airborne surplus power generation capacity utilization subsystem is connected with the closed air compression circulation subsystem through the motor; the closed air compression circulation subsystem is connected with the local power grid power supply storage subsystem through a generator (103); the closed air compression circulation subsystem is connected with the oil-immersed cold energy storage and supply subsystem through a gas-liquid low-temperature heat exchanger (204); the local power grid power supply storage subsystem is connected with the oil-immersed cold energy storage supply subsystem through a pump motor (403).
The airborne surplus power generation capacity utilization subsystem is a circuit system and comprises: an aircraft electrical grid (101), a base electrical load (102), an electric motor (103), and circuit wiring. The electrical energy provided by the aircraft electrical network (101) is used to satisfy the basic electrical loads (103) and the electric motor (103) on board the aircraft. The electric motor (103) converts electric energy into mechanical energy, and the shaft work is transmitted through the transmission shaft to drive the closed air compression circulation subsystem.
The closed air compression circulation subsystem is a gas phase circulation system comprising: the system comprises a compressor (201), a gas-gas high-temperature heat exchanger (202), an expansion turbine (203), a gas-liquid low-temperature heat exchanger (204), a heat exchanger gas-phase pipeline (205), ram air, a connecting pipeline and internal air. The gas-gas high-temperature heat exchanger (202) carries out gas-gas heat exchange on high-temperature and high-pressure air and ram air compressed by the compressor (201), the temperature is reduced again through the expansion turbine (203), the high-temperature and high-pressure air reaches the gas-phase pipeline (205) of the heat exchanger through the connecting pipeline, and cold energy is transferred to the liquid-phase pipeline (401) through the gas-liquid low-temperature heat exchanger (204).
The local grid power supply storage subsystem is a circuit system comprising: a generator (301), a local grid (302), a battery pack (303), and a wiring circuit. The high-pressure air impact expansion turbine (203) in the closed air compression circulation subsystem is changed into low-pressure air, the low-pressure air impacts the expansion turbine to generate mechanical energy by doing axial work, a generator (301) is driven, the mechanical energy is converted into electric energy, the electric energy is stored in an onboard storage battery pack (303) through a local power grid, and the stored electric energy is used for driving a pump motor (403) to do work.
The oil-immersed cold energy storage and supply subsystem is a liquid phase circulating system and comprises: a liquid phase pipeline (401), a pump (402) and a pump motor (40) in the gas-liquid low-temperature heat exchanger (204)
) The system comprises a first check valve (404), a high-power thermal load (405), a second check valve (406), a first oil-immersed heat exchanger (407), a cold accumulation oil tank (408), a second oil-immersed heat exchanger (409), a third check valve (410), a connecting pipeline and PAO oil in the pipeline. Energy in the gas-liquid low-temperature heat exchanger (204) is transmitted to two paths by a pump (402) driven by a pump motor (403) through a liquid phase pipeline (401): one path is directly supplied to a high-power heat load (405) for cooling; the other path is connected to a cold accumulation oil tank (408) to store cold energy and provide a cold energy end. And a second oil-immersed heat exchanger (409) in the cold accumulation oil tank (408) is connected with the high-power heat load (405) and is used for supplementing cold energy.
The pump (402) of the oil-immersed cold energy storage and supply subsystem is driven by a pump motor (403), and the electric energy of the pump motor (403) is provided by a storage battery pack (303) in the power supply and storage subsystem of the local power grid (302).
The oil-immersed cold energy storage and supply subsystem has three working modes: firstly, cold energy carried by PAO oil conveyed by a pump is directly supplied to a high-power heat load for cooling and heat dissipation, as shown in FIG. 3; secondly, on the premise that the cold energy required by the high-power heat load is enough, the cold energy carried by the PAO oil conveyed by the pump reaches the cold accumulation oil tank (408) through the second one-way valve (406), and the cold energy is stored, as shown in FIG. 4; thirdly, when the cold energy required by the high-power electronic equipment is insufficient, the cold energy of the PAO oil in the cold storage oil tank is supplemented to the high-power electronic equipment (405) through the third check valve (410), so that the problem of insufficient cold energy supply is solved, as shown in fig. 5. The whole oil-immersed cold energy storage and supply subsystem has strong in-system self-regulation capacity.
The invention integrates the characteristics of the system, and has the beneficial effects that:
on the premise of ensuring the power supply of the airplane load, the surplus power generation capacity of the airplane power grid (101) is fully utilized, the electric energy is converted into cold energy, the airplane electric energy is utilized to the maximum extent, the electric energy utilization rate is improved, and the energy scheduling is realized;
the closed air compression circulation subsystem is adopted, the design requirements of a future multi-electric/full-electric airplane are met, shaft work output by air compression circulation is fully utilized, mechanical energy is converted into electric energy through the generator (301), the electric energy is transmitted to the airplane local power grid (302), the electric energy is stored in the storage battery pack (303) and serves as a supply source of the electric energy of the pump motor (403), and the storage and the supply of the electric energy are realized;
the defect that the airplane depends on ram air as the main heat sink of the airplane is overcome;
the development bottleneck of insufficient airborne cold energy of a multi-electric/full-electric airplane in the future is solved, and the problems of airplane cold energy storage, reasonable utilization and cold energy supply when the cold energy is insufficient are solved;
the oil-immersed cold energy storage and supply subsystem has strong self-regulation capability.
The invention is further illustrated by the following specific embodiments.
With reference to the schematic diagram of fig. 1, the system of the present invention mainly includes four subsystems: the system comprises an airplane airborne surplus power generation capacity utilization subsystem, a closed air compression circulation subsystem, a local power grid power supply storage subsystem and an oil-immersed cold energy storage and supply subsystem.
In fig. 1, the onboard surplus power generation utilization system of the aircraft belongs to a circuit system, and comprises: an aircraft electrical network (101), a basic onboard electrical load (102), an electric motor (103) and circuit wiring. The electrical energy provided by the aircraft electrical network (101) is used to satisfy the basic electrical loads (102) and the electric motor 103 on board the aircraft. The aircraft electrical network (101) will first satisfy the base electrical load (102), and the surplus electrical power generation capacity is used to drive the electric motor (103). The electric motor (103) converts electric energy into mechanical energy, and the shaft work is transmitted through the transmission shaft to drive the closed air compression circulation subsystem.
In fig. 1, the closed air compression cycle subsystem belongs to a gas phase cycle system, which comprises: the system comprises a compressor (201), a gas-gas high-temperature heat exchanger (202), an expansion turbine (203), a gas-liquid low-temperature heat exchanger (204) and a gas phase pipeline 205 of the gas-liquid low-temperature heat exchanger, ram air, a connecting pipeline and internal air. The gas-gas high-temperature heat exchanger (202) carries out gas-gas heat exchange on high-temperature high-pressure air and ram air compressed by the compressor (201), the high-temperature high-pressure air and the ram air are cooled again through the expansion turbine (203) and reach the gas-phase pipeline (205) of the heat exchanger through the connecting pipeline, cold energy is transmitted to the liquid-phase pipeline (401) through the gas-liquid low-temperature heat exchanger (204), the gas-phase outlet of the gas-liquid low-temperature heat exchanger (204) is connected with the inlet of the compressor (201), and the whole air compression circulating system is in.
In fig. 1, the local grid power supply storage subsystem is a circuit system, which includes: a generator (301), a local grid (302), a battery pack (303), and a wiring circuit. High-pressure air in the closed air compression circulation subsystem impacts the expansion turbine (203) to become low-pressure air, does shaft work to generate mechanical energy, drives the generator (301), converts the mechanical energy into electric energy, and stores the electric energy into the onboard storage battery pack (303) through the local power grid (302).
In the local power grid power supply storage subsystem, a storage battery pack (303) is connected with a pump motor (403) in the oil-immersed cold energy storage and supply subsystem, and electric energy stored in the storage battery pack (303) is used for driving the pump motor (403) to do work.
In fig. 1, the oil-immersed cold energy storage and supply subsystem is a liquid phase circulation system including: the device comprises a liquid phase pipeline (401) in the gas-liquid low-temperature heat exchanger (204), a pump (402), a pump motor (403), a first check valve (404), a first oil-immersed heat exchanger (407), a cold accumulation oil tank (408), a second oil-immersed heat exchanger (409), a second check valve (406), a high-power heat load (405), a third check valve (410), a connecting pipeline and PAO oil liquid in the pipeline. The first check valve (404) controls the flow of PAO oil in one path of the high-power heat load so as to control the cold energy required by the high-power heat load; the second check valve (406) controls the flow of PAO oil at one path of the cold accumulation oil tank so as to control the amount of cold energy stored in the cold accumulation oil tank; the third check valve (410) controls the flow of PAO oil from the cold accumulation oil tank to the high-power heat load, so as to control the supply of cold energy from the cold accumulation oil tank to the high-power heat load.
The operation logic of the whole system is shown in fig. 2, and the operation mode of the whole system is explained by combining with the operation logic diagram. The airplane power grid (101) supplies power to the airborne basic electric load (102), whether the requirement of the basic electric load (102) is met is judged, if the requirement is not met, surplus power generation capacity does not exist, and the basic electric load is continuously supplied with power; if the requirement is satisfied, the generated surplus power generation capacity is used for driving the motor (103). The electric motor (103) converts electric energy into rotary mechanical energy for driving the closed air compression cycle system to refrigerate, shaft work output by the expansion turbine (203) is converted into electric energy through the generator (301), and the electric energy is stored in the storage battery pack (303) through the local power grid (302) so as to meet the electric energy requirement of the pump motor (403). The pump motor (403) drives the pump (402) to convey cold energy carried in the PAO oil to the oil-immersed cold energy storage supply subsystem. The cold energy firstly meets the heat dissipation and cooling requirements of the high-power heat load (405), redundant cold energy is stored in the cold accumulation oil tank (408) to provide a cold end on the premise of meeting the requirements, and when the cold energy requirement of the high-power heat load (405) is insufficient, the cold accumulation oil tank (408) supplements the cold energy to the high-power heat load (405).
Energy in the gas-liquid low-temperature heat exchanger (204) is transmitted to two paths by a pump (402) through a liquid phase pipeline (401): one path is directly supplied to a high-power heat load for cooling; and the other path is transmitted to the second oil-immersed heat exchanger through PAO oil liquid and then to a cold accumulation oil tank (408) to store cold energy and provide a cold energy end. And a third oil-immersed heat exchanger in the cold accumulation oil tank (408) is connected with a high-power heat load and used for supplementing cold energy.
The oil-immersed cold energy storage and supply subsystem has three working modes, firstly, as shown in fig. 3, a pump (402) conveys PAO oil, and cold energy carried by the oil is directly supplied to a high-power heat load (405) for cooling through a first check valve (404); secondly, as shown in fig. 4, on the premise that the cold energy required by the high-power heat load (405) is enough, the pump (402) delivers the cold energy carried by the PAO oil to the cold accumulation oil tank (408) through the second check valve (406), and the cold energy is stored; thirdly, as shown in fig. 5, when the cold energy required by the high-power heat load (405) is insufficient, the cold energy of the high-power heat load (405) is supplemented by the PAO oil in the cold storage oil tank (408) through the third check valve (410), so that the problem of insufficient cold energy supply is alleviated. The three working modes are coordinated and controlled mutually, so that the strong self-regulation capability of the whole oil-immersed cold energy storage and supply subsystem is realized.
Claims (10)
1. The utility model provides a surplus generating capacity utilizes system based on closed air compression circulation which characterized in that includes:
an electric motor (103) for converting electrical energy of the aircraft electrical network (101) into mechanical energy,
a compressor (201) operated by the motor (103),
the air-air high-temperature heat exchanger (202) is used for carrying out air-air heat exchange on high-temperature and high-pressure air compressed by the compressor and ram air,
an expansion turbine (203), the gas from the gas-gas high-temperature heat exchanger (202) is cooled again through the expansion turbine (203),
a gas-liquid low-temperature heat exchanger (204), wherein gas from the expansion turbine (203) reaches a gas-phase pipeline (205) of the gas-liquid low-temperature heat exchanger (204) through a connecting pipeline so as to transfer cold energy to oil liquid in a liquid-phase pipeline (401) of the gas-liquid low-temperature heat exchanger (204),
a generator (301) operated by the expansion turbine (203),
a battery pack (303) for storing electric energy generated by the generator (301),
a pump motor (403) which operates by being driven by electric power from the battery pack (303),
a pump (402) which is driven by a pump motor (403) to operate and drive the oil,
a cold storage tank (408) for holding a liquid as a heat sink,
a first oil-immersed heat exchanger (407) for exchanging heat between the oil from the pump (402) and the heat sink in the cold storage tank (408),
a first oil line from the pump (402) to the liquid phase line (401) via a thermal load (405),
a second oil line from the pump (402) to the liquid phase line (401) via the first oil-immersed heat exchanger,
a second check valve (406) disposed on the second oil line,
a second oil-immersed heat exchanger (409) for exchanging heat between the oil flowing through the second oil-immersed heat exchanger and the heat sink in the cold storage oil tank (408),
and the third check valve (410), wherein the second oil-immersed heat exchanger (409), the third check valve (410) and the thermal load (405) are connected into an oil circuit through an additional oil pipeline.
2. The surplus power generation capacity utilization system according to claim 1, characterized in that:
the oil is a polyalphaolefin oil,
the liquid acting as a heat sink is fuel oil.
3. The surplus power generation capacity utilization system according to claim 1 or 2, characterized in that:
when the power supply of the airplane power grid (101) does not meet the requirement of the on-board basic electric load (102), the electric motor (103) does not work, and when the power supply of the airplane power grid (101) meets the requirement of the on-board basic electric load (102), the electric motor (103) works under the driving of surplus electric power of the airplane power grid.
4. The surplus power generation capacity utilization system according to claim 3, characterized in that:
when the cold energy provided by the first oil liquid pipeline can meet the heat dissipation of the heat load (405) and the surplus cold energy exists, the surplus cold energy is stored in the heat sink in the cold accumulation oil tank (408) through the second oil liquid pipeline and the first oil-immersed heat exchanger by controlling the second one-way valve (406),
when the cold energy provided by the first oil liquid pipeline cannot meet the heat dissipation of the heat load (405), the third check valve (410) is controlled, so that the high-power heat load exchanges heat with the heat sink in the cold accumulation oil tank (408) through the oil liquid in the additional oil liquid pipeline and the second oil-immersed heat exchanger (409).
5. The surplus power generation capacity utilization system according to claim 1 or 2, characterized by further comprising:
a first one-way valve (404) disposed on the first oil line.
6. A surplus power generation capacity utilization method based on closed air compression circulation is characterized by comprising the following steps:
converting the electrical energy of the aircraft electrical network (101) into mechanical energy by means of the electric motor (103),
the compressor (201) is driven by the electric energy generated by the motor (103),
the high-temperature and high-pressure air compressed by the compressor (201) and the ram air are subjected to air-air heat exchange by the air-air high-temperature heat exchanger (202),
the gas from the gas-gas high-temperature heat exchanger (202) is cooled again through expansion by an expansion turbine (203),
the gas from the expansion turbine (203) is led to a gas phase pipeline (205) of the gas-liquid low-temperature heat exchanger (204) through a connecting pipeline, so that the cold energy is transferred to the oil liquid in a liquid phase pipeline (401) of the gas-liquid low-temperature heat exchanger (204),
the generator (301) is driven by the expansion turbine (203) to work,
the storage battery pack (303) is used for storing the electric energy generated by the generator (301),
the pump motor (403) is driven by the electric power from the battery pack (303) to operate,
the pump (402) is driven by a pump motor (403) to operate, and drives the oil,
a cold storage oil tank (408) is used for containing liquid used as a heat sink,
the oil liquid from the pump (402) is subjected to heat exchange with the heat sink in the cold accumulation oil tank (408) by the first oil-immersed heat exchanger (407),
a first oil line is connected from the pump (402) to the liquid line (401) via a thermal load (405),
connecting a second oil line from the pump (402) to the liquid phase line (401) via the first oil-immersed heat exchanger (407),
a second one-way valve (406) is disposed on the second oil line,
the oil liquid flowing through the second oil-immersed heat exchanger (409) is subjected to heat exchange with the heat sink in the cold accumulation oil tank (408),
and the second oil-immersed heat exchanger (409), the third check valve (410) and the thermal load (405) are connected into an oil liquid loop through an additional oil liquid pipeline.
7. The surplus power generation capacity utilization method according to claim 6, characterized in that:
the oil is a polyalphaolefin oil,
the liquid acting as a heat sink is fuel oil.
8. The surplus power generation capacity utilization method according to claim 6 or 7, characterized by further comprising:
determining whether the power supply of the aircraft power grid (101) meets the requirements of the on-board base electrical load (102),
stopping the operation of the electric motor (103) when the power supply of the aircraft power grid (101) does not meet the demand of the on-board elementary electric load (102),
when the power supply of the airplane power grid (101) meets the requirement of the on-board basic electric load (102), the electric motor (103) is driven to work by surplus electric power of the airplane power grid (101).
9. The surplus power generation capacity utilization method according to claim 8, characterized by further comprising:
whether the cold energy provided by the first oil pipeline meets the heat dissipation of the heat load (405) or not is judged,
when the cold energy provided by the first oil liquid pipeline can meet the heat dissipation of the heat load (405) and the surplus cold energy exists, the surplus cold energy is stored in the heat sink in the cold accumulation oil tank (408) through the second oil liquid pipeline and the first oil-immersed heat exchanger by controlling the second one-way valve (406),
when the cold energy provided by the first oil liquid pipeline cannot meet the heat dissipation of the heat load (405), the third check valve (410) is controlled, so that the high-power heat load exchanges heat with the heat sink in the cold accumulation oil tank (408) through the oil liquid in the additional oil liquid pipeline and the second oil-immersed heat exchanger (409).
10. The surplus power generation capacity utilization method according to claim 6 or 7, characterized by further comprising:
a first check valve (404) is disposed on the first oil line.
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| JP4113644B2 (en) * | 2000-01-24 | 2008-07-09 | 東京瓦斯株式会社 | City gas high-pressure storage method and storage equipment |
| CN204555419U (en) * | 2015-03-13 | 2015-08-12 | Tcl空调器(中山)有限公司 | Air-conditioning system |
| CN105179033B (en) * | 2015-08-12 | 2017-05-31 | 中国科学院工程热物理研究所 | The system and its operation method of a kind of utilization cryogenic cold energy storage electric energy |
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