CN114906332B - Airborne pump drive energy utilization system - Google Patents
Airborne pump drive energy utilization system Download PDFInfo
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- CN114906332B CN114906332B CN202210543994.6A CN202210543994A CN114906332B CN 114906332 B CN114906332 B CN 114906332B CN 202210543994 A CN202210543994 A CN 202210543994A CN 114906332 B CN114906332 B CN 114906332B
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- 239000003507 refrigerant Substances 0.000 claims abstract description 114
- 239000007788 liquid Substances 0.000 claims abstract description 104
- 238000010438 heat treatment Methods 0.000 claims abstract description 93
- 238000001816 cooling Methods 0.000 claims abstract description 80
- 230000017525 heat dissipation Effects 0.000 claims abstract description 17
- 239000000110 cooling liquid Substances 0.000 claims abstract description 16
- 230000005611 electricity Effects 0.000 claims abstract description 12
- 238000004146 energy storage Methods 0.000 claims description 14
- 239000002826 coolant Substances 0.000 claims description 11
- 230000005494 condensation Effects 0.000 claims description 10
- 238000009833 condensation Methods 0.000 claims description 10
- 238000004064 recycling Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 25
- 238000005516 engineering process Methods 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 239000000284 extract Substances 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0644—Environmental Control Systems including electric motors or generators
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0648—Environmental Control Systems with energy recovery means, e.g. using turbines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
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- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Electromagnetic Pumps, Or The Like (AREA)
Abstract
The invention discloses an airborne pump driving energy utilization system which comprises a pump driving loop, a main cooling loop and a radiator, wherein the main cooling loop comprises a liquid cooling liquid storage tank, a liquid cooling pump, heating equipment and a liquid cooling radiator. The pump driving loop comprises a refrigerant liquid storage tank, a refrigerant pump, an expander, an electric storage device, a first valve, a second valve, a heating device, a fourth valve, a third valve and a second condenser. The electricity storage equipment is communicated with the air outlet end of the expander and is used for performing expansion work according to the expansion gas to obtain and store electric energy; the heating equipment is arranged in the aircraft cabin and is communicated with the air outlet end of the expander, and the heating equipment is used for heating the aircraft cabin by the refrigerant gas which passes through the first valve and carries all heat or the refrigerant gas which passes through the expander and carries the residual heat after being expanded to obtain the refrigerant liquid. The energy recycling is realized, and the difficulty of cooperative heat dissipation of airborne equipment is improved.
Description
Technical Field
The invention relates to the technical field of aircraft environment control, in particular to an airborne pump driving energy utilization system.
Background
With the continuous improvement of the performance of an airplane, the heating value of each device in the electromechanical system of the airplane is increased. At present, various cooling technologies are still adopted to take away the heat of equipment and discharge the heat out of the aircraft, and the utilization rate of the on-board energy is very low. Therefore, a design idea of comprehensive heat management of an aircraft is needed to develop an onboard energy utilization system to fully recover the waste heat of onboard equipment. Pump drive technology based on single-phase flow is fully utilized in aircraft main cooling circuits, but has not been involved in energy utilization. Therefore, there is a need to study on-board pump drive energy utilization systems that are reasonably well-distributed.
Disclosure of Invention
The invention aims to provide an airborne pump driving energy utilization system, which realizes the cyclic utilization of energy and improves the cooperative heat dissipation performance of airborne equipment.
In order to achieve the above object, the present invention provides the following solutions:
An on-board pump drive energy utilization system coupled to an aircraft cabin, the on-board pump drive energy utilization system comprising:
A heat collector;
A primary cooling circuit, the primary cooling circuit comprising:
The liquid cooling liquid storage tank is used for storing the secondary refrigerant;
the liquid cooling pump is communicated with the liquid cooling liquid storage tank and is used for extracting the secondary refrigerant;
The heating equipment is respectively communicated with the liquid cooling pump and the heat collector and is used for heating the secondary refrigerant and transmitting the heated secondary refrigerant to the heat collector; the heat collector is used for heating the refrigerant liquid by utilizing part of heat in the heated secondary refrigerant and transmitting the secondary refrigerant carrying the rest part of heat to the liquid cooling radiator;
The liquid cooling radiator is respectively communicated with the liquid cooling liquid storage tank and the heat collector and is used for cooling the secondary refrigerant carrying the rest heat and transmitting the cooled secondary refrigerant to the liquid cooling liquid storage tank;
A pump drive circuit, the pump drive circuit comprising:
the refrigerant liquid storage tank is used for storing a refrigerant;
the refrigerant pump is respectively communicated with the refrigerant liquid storage tank and the heat collector and is used for extracting the refrigerant liquid from the refrigerant and transmitting the refrigerant liquid to the heat collector;
The air inlet end of the expander is communicated with the heat collector and is used for receiving the refrigerant gas formed by heating the refrigerant liquid by the heat collector to expand so as to obtain expanded gas;
the electricity storage equipment is communicated with the air outlet end of the expander and is used for performing expansion work according to the expansion gas to obtain and store electric energy;
The first valve is connected in parallel to the energy storage pipeline which is communicated with the air outlet end of the expander and is used for controlling the turn-off of the energy storage pipeline;
the second valve is arranged on the energy storage pipeline which is communicated with the air inlet end of the expander and used for controlling the turn-off of the energy storage pipeline;
The heating device is arranged in the aircraft cabin, is communicated with the air outlet end of the expander and is used for heating the aircraft cabin by the refrigerant gas which passes through the first valve and carries all heat or the refrigerant gas which passes through the expander and carries the residual heat after being expanded to obtain refrigerant liquid;
the fourth valve is communicated in parallel with a heating pipeline of which the air outlet end is communicated with the heating equipment and is used for controlling the turn-off of the heating pipeline;
the third valve is arranged on a heating pipeline which is communicated with the air outlet end of the expander through the heating equipment and is used for controlling the turn-off of the heating pipeline;
The second condenser is respectively communicated with the fourth valve, the heating equipment and the refrigerant liquid storage tank and is used for carrying out condensation heat release on the refrigerant gas flowing through the fourth valve to obtain refrigerant liquid or enabling the refrigerant liquid obtained from the heating equipment to flow back into the refrigerant liquid storage tank.
Optionally, the power storage device includes:
a generator which is communicated with the expander and is used for generating electricity by the gas expanded by the expander;
and the storage battery is connected with the generator and used for storing the power generated by the generator.
Optionally, the heating device includes:
the first condenser is respectively connected with the third valve and the air inlet end of the second condenser and is used for condensing and releasing heat of refrigerant gas carrying residual heat after the expansion of the expander;
And the fan is positioned at one side of the first condenser and used for transmitting heat discharged by condensation of the first condenser to all parts of the cabin.
Optionally, the heat generating device includes: the heating elements are communicated in parallel between the liquid cooling pump and the heat collector.
Optionally, the heat generating device further includes: and each equipment flowmeter is respectively arranged between the heating element and the liquid cooling pump.
Optionally, the main cooling circuit further comprises:
The first bypass valve is arranged on a bypass pipeline which is connected in parallel and communicated with the air outlet end of the liquid cooling radiator and the air inlet end of the second condenser and used for controlling the on-off of the bypass pipeline.
Optionally, the main cooling circuit further comprises:
A bypass flow meter disposed on the bypass conduit for measuring flow through the bypass conduit;
an eleventh temperature and pressure sensor is disposed on the bypass conduit for measuring temperature and pressure through the bypass conduit.
Optionally, the main cooling circuit further comprises:
the liquid cooling flowmeter is arranged between the liquid cooling pump and the equipment flowmeter and is used for measuring the flow of the secondary refrigerant;
and a sixth temperature and pressure sensor, disposed between the liquid cooling pump and the equipment flow meter, for measuring the temperature and pressure of the coolant.
Optionally, the pump drive circuit further comprises:
The second bypass valve is arranged on a heat dissipation pipeline communicated with the air outlet end of the second condenser and the air inlet end of the liquid cooling radiator and used for controlling the on-off of the heat dissipation pipeline.
Optionally, the pump drive circuit further comprises:
And a twelfth temperature and pressure sensor provided on the heat dissipation pipe for measuring the temperature and pressure flowing through the heat dissipation pipe.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention relates to an airborne pump driving energy utilization system, which comprises a pump driving loop, a main cooling loop and a radiator, wherein heat is exchanged between the main cooling loop and the pump driving loop through a heat collector, so that heat generated in the main cooling loop is transferred into the pump driving loop, and the purposes of energy conversion, heating and heat dissipation are finally achieved through arranging energy storage equipment and heating equipment in the pump driving loop, so that the problem of cooperative heat dissipation of airborne equipment and the conversion of energy utilization are solved. The airborne pump driving energy utilization system solves the problem of low airborne energy utilization rate of the aircraft, is more in line with the design thought of comprehensive thermal management of the aircraft, and realizes the technical innovation of the electromechanical system of the aircraft. The invention designs the configuration and the control strategy of the energy utilization system of the pump drive on the aircraft, and utilizes the technologies of evaporation, condensation, expansion work, energy storage and the like to ensure that the heat of the equipment on the aircraft is efficiently recycled.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of an airborne pump driving energy utilization system according to an embodiment of the present invention.
Symbol description:
1-refrigerant pump, 2-heat collector, 3-expander, 4-generator, 5-first condenser, 6-fan, 7-second condenser, 8-refrigerant reservoir, 9-battery, 10-heat generating device, 11-first valve, 12-second valve, 13-third valve, 14-fourth valve, 15-refrigerant flow meter, 16-first temperature and pressure sensor, 17-second temperature and pressure sensor, 18-third temperature and pressure sensor, 19-fourth temperature and pressure sensor, 20-fifth temperature and pressure sensor, 21-liquid cooling pump, 22-first heat generating element, 23-second heat generating element, 24-third heat generating element, 25-liquid cooling radiator, 26-liquid cooling reservoir, 27-first bypass valve, 28-liquid cooling flow meter, 29-bypass flow meter, 30-first device flow meter, 31-second device flow meter, 32-third device flow meter, 33-sixth temperature and pressure sensor, 34-seventh temperature and pressure sensor, 35-eighth temperature and pressure sensor, 36-ninth temperature and pressure sensor, 36-tenth temperature and pressure sensor, and eleventh temperature and eleventh pressure sensor.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide an airborne pump driving energy utilization system, which realizes energy recycling and improves the airborne cooperative heat dissipation capacity.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1, the on-board pump drive energy utilization system of the present invention is connected to an aircraft cabin. The airborne pump driving energy utilization system comprises a heat collector 2, a main cooling loop and a pump driving loop.
Specifically, the main cooling circuit includes a liquid cooling liquid storage tank 26, a liquid cooling pump 21, a heating device 10, and a liquid cooling radiator 25. Wherein the liquid-cooled receiver tank 26 is configured to store coolant. The liquid cooling pump 21 is communicated with the liquid cooling liquid storage tank 26, and the liquid cooling pump 21 is used for pumping out the secondary refrigerant. The heating device 10 is respectively communicated with the liquid cooling pump 21 and the heat collector 2, and the heating device 10 is used for heating the secondary refrigerant and transmitting the heated secondary refrigerant to the heat collector 2; the heat collector 2 is configured to heat the coolant liquid by using a part of heat in the heated coolant, and transfer the coolant carrying the rest of heat to the liquid-cooled radiator 25.
The liquid cooling radiator 25 is respectively communicated with the liquid cooling liquid storage tank 26 and the heat collector 2, the liquid cooling radiator 25 is used for cooling the secondary refrigerant carrying the rest heat, and the liquid cooling radiator 25 transmits the cooled secondary refrigerant to the liquid cooling liquid storage tank 26.
The pump driving loop comprises a refrigerant liquid storage tank 8, a refrigerant pump 1, an expander 3, an electric storage device, a first valve 11, a second valve 12, a heating device 10, a fourth valve 14, a third valve 13 and a second condenser 7.
The refrigerant liquid storage tank 8 is used for storing refrigerant. The refrigerant pump 1 is respectively communicated with the refrigerant liquid storage tank 8 and the heat collector 2, and the refrigerant pump 1 is used for pumping out refrigerant liquid from the refrigerant and transmitting the refrigerant liquid to the heat collector 2. The air inlet end of the expander 3 is communicated with the heat collector 2, and the expander 3 is used for receiving the refrigerant gas formed by heating the refrigerant liquid by the heat collector 2 to expand so as to obtain expanded gas. The electricity storage equipment is communicated with the air outlet end of the expander 3 and is used for performing expansion work according to the expansion gas to obtain and store electric energy; the first valve 11 is connected in parallel to an energy storage pipeline which is communicated with the air outlet end of the expander 3 and the heat collector 2, and the first valve 11 is used for controlling the turn-off of the energy storage pipeline; the second valve 12 is arranged on an energy storage pipeline which is communicated with the air inlet end of the expander 3 and the heat collector 2, and the second valve 12 is used for controlling the turn-off of the energy storage pipeline; the heating device 10 is arranged in the aircraft cabin, the heating device 10 is communicated with the air outlet end of the expander 3, and the heating device 10 is used for heating the aircraft cabin by all heat refrigerant gas carried by the first valve 11 or the refrigerant gas carrying residual heat after being expanded by the expander 3 to obtain refrigerant liquid. The fourth valve 14 is connected in parallel to a heating pipeline connected with the heating device 10 at the air outlet end of the expander 3, and the fourth valve 14 is used for controlling the turn-off of the heating pipeline. The third valve 13 is arranged on a heating pipeline of the heating device 10 communicated with the air outlet end of the expander 3, and the third valve 13 is used for controlling the shutoff of the heating pipeline; the second condenser 7 is respectively communicated with the fourth valve 14, the heating device 10 and the refrigerant liquid storage tank 8, and the second condenser 7 is used for condensing and releasing heat of the refrigerant gas flowing through the fourth valve 14 to obtain refrigerant liquid or flowing the refrigerant liquid obtained from the heating device 10 back to the refrigerant liquid storage tank 8.
In the invention, the main cooling loop transfers heat to the refrigerant through evaporation and absorption, and the pump driving loop transfers heat to the refrigerant through condensation and release.
Specifically, the heating device comprises a first condenser 5 and a fan 6. The first condenser 5 is respectively connected with the third valve 13 and the air inlet end of the second condenser 7, and the first condenser 5 is used for condensing and releasing heat of refrigerant gas carrying residual heat after the expansion of the expander. The fan 6 is located at one side of the first condenser 5, and the fan 6 is used for transferring heat released by condensation of the first condenser 5 to various places of the cabin.
The first condenser 5 and the fan 6 are placed in the aircraft cabin and transfer heat to the cabin air by means of the heat of condensation giving up its temperature.
Preferably, the heating device comprises a plurality of heating elements, and each heating element is communicated in parallel between the liquid cooling pump and the heat collector. In this embodiment, the number of the heating elements is three, namely the first heating element 22, the second heating element 23, and the third heating element 24.
Further, in order to monitor the flow passing condition in each heating element in real time, the heating device further comprises a plurality of device flow meters, and each device flow meter is respectively arranged between the heating element and the liquid cooling pump. In the invention, by correspondingly connecting each equipment flowmeter and each heating element, the heating elements in each group can be better evenly distributed to the flow, so that more uniform heating is realized. Specifically, the heat of the first heating element 22, the second heating element 23 and the third heating element 24 is absorbed by the coolant, and then transferred to the coolant in the pump driving loop through the heat collector 2; the remaining heat in the coolant is transferred by the liquid-cooled heat sink 25 to a heat sink such as ram air or fuel.
Optionally, the electricity storage device comprises a generator 4 and a storage battery 9. The generator 4 is communicated with the expander 3, and the generator 4 is used for driving the generator 4 to generate electricity through expansion work by the gas expanded by the expander 3, and storing electric energy in the storage battery 9.
Optionally, the main cooling circuit further comprises a bypass flow meter 29, an eleventh temperature and pressure sensor 38. The bypass flow meter 29 is arranged on the bypass conduit for measuring the flow through the bypass conduit. The eleventh temperature and pressure sensor 38 is provided on the bypass conduit for measuring the temperature and pressure through the bypass conduit.
Optionally, the main cooling circuit further comprises: a liquid-cooled flow meter 28, a sixth temperature and pressure sensor 33. The liquid-cooled flowmeter 28 is disposed between the liquid-cooled pump 21 and the equipment flowmeter for measuring the flow rate of the coolant. The sixth temperature and pressure sensor 33 is disposed between the liquid cooling pump 21 and the equipment flow meter for measuring the temperature and pressure of the coolant.
Optionally, the pump drive circuit further comprises a twelfth temperature and pressure sensor 39. The twelfth temperature and pressure sensor 39 is provided on the heat dissipation pipe for measuring the temperature and pressure flowing through the heat dissipation pipe.
Specifically, when the aircraft cabin does not need to be warmed, the third valve 13 and the fan 6 are closed, and the fourth valve 14 is opened; when the cabin needs to be warmed, the fourth valve 14 is closed, and the third valve 13 and the fan 6 are opened; when the heating amount required by the cabin is large, the second valve 12 is closed, and the first valve 11 is opened, so that the heat extracted by the pump driving circuit is completely used for heating the cabin; when the heating amount required by the cabin is small, the first valve 11 is closed, and the second valve 12 is opened, so that the heat extracted by the pump driving circuit is firstly used for generating electricity and then used for heating the cabin.
Optionally, the main cooling circuit further comprises a first bypass valve 27. The first bypass valve 27 is arranged on a bypass pipeline which is connected in parallel between the air outlet end of the liquid cooling radiator 25 and the air inlet end of the second condenser 7, and the first bypass valve 27 is used for controlling the on-off of the bypass pipeline. When the fourth valve 14 is open, the first bypass valve 27 is open and vice versa.
As an embodiment, the pump drive circuit further comprises a second bypass valve 40. The second bypass valve is disposed on a heat dissipation pipe that communicates between the air outlet end of the second condenser 7 and the air inlet end of the liquid cooling radiator 25, and the second bypass valve 40 is used for controlling on-off of the heat dissipation pipe.
The refrigerant pump 1 in the pump driving loop extracts the refrigerant from the refrigerant liquid storage tank 8, the refrigerant gas is heated to a full gas phase state through the heat collector 2, then the refrigerant gas enters the expander 3 to expand and do work, the generator 4 is driven to generate electricity and stored in the storage battery 9, the expanded gas enters the first condenser 5, heat is transferred to cabin air through condensation heat release, then enters the second condenser 7, and finally flows back to the refrigerant liquid storage tank 8.
The liquid cooling pump 21 in the main cooling loop extracts the secondary refrigerant from the liquid cooling liquid storage tank 26, the secondary refrigerant is heated by heating equipment, the heated secondary refrigerant then enters the heat collector 2, heat is transferred to the refrigerant liquid in the refrigerant liquid pump driving loop in the pump driving loop, the refrigerant liquid is heated into refrigerant gas by the heat collector 2, the circulation of the refrigerant gas in the pump driving loop is carried out according to the requirement of whether the cabin is heated or not, then the residual heat of the secondary refrigerant in the main cooling loop enters the liquid cooling radiator 25, the heat is transferred to heat sinks such as ram air or fuel oil, and finally the heat flows back to the liquid cooling liquid storage tank 26.
The main cooling circuit is also connected to the second condenser 7 of the pump drive circuit by a first bypass valve 27; when the fourth valve 14 is open, the first bypass valve 27 is open and vice versa.
When the cabin does not need to be heated, the fourth valve 14 and the first bypass valve 27 in the pump driving loop are simultaneously opened, the first valve 11 is in a closed state, at the moment, the refrigerant gas enters the expander 3 through the second valve 12 to expand and apply work to drive the generator 4 to generate electricity and store the heat into the storage battery 9, the residual refrigerant gas heat flows to the second condenser 7 through the fourth valve 14, the heat is released through the condensation of the second condenser 7 and finally returns to the refrigerant storage tank 8, at the moment, the residual heat left after passing through the heat collector 2 in the main cooling loop is transferred to the heat sink through the liquid cooling radiator, and then flows to the second condenser 7 through the first bypass valve 27 and finally flows back to the refrigerant storage tank 8. At this time, the pump driving circuit is mainly used for storing energy first, when the cabin needs to increase a lot of heat, the first bypass valve 27 and the fourth valve 14 are closed at the same time, the second valve 12 is also closed, all heat carried by refrigerant gas is used for heating the cabin, heat carried by the secondary refrigerant passing through the heat collector 2 in the main cooling circuit is transferred to the ram air or the fuel oil and other heat sinks through the liquid cooling radiator 25, and finally flows back to the liquid cooling liquid storage tank 26.
When the heating value of the heating equipment changes, the rotation speed of the liquid cooling pump 21 changes, and the flow of the main cooling circuit is changed, so that the flow flowing through the heating equipment is matched with the heating value of the heating equipment. Meanwhile, the secondary refrigerant also plays a role in cooling in the heating equipment.
When the cabin does not need to be warmed, the third valve 13 and the fan 6 are closed, and the fourth valve 14 is opened; when the cabin needs to be warmed, the fourth valve 14 is closed, and the third valve 13 and the fan 6 are opened; when the heating amount required by the cabin exceeds a threshold value, the second valve 12 is closed, and the first valve 11 is opened, so that the heat extracted by the pump driving circuit is completely used for heating the cabin; when the heating amount required by the cabin is smaller than the threshold value, the first valve 11 is closed, and the second valve 12 is opened, so that the heat extracted by the pump driving circuit is firstly used for generating electricity and then used for heating the cabin.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (10)
1. An on-board pump drive energy utilization system coupled to an aircraft cabin, the on-board pump drive energy utilization system comprising:
A heat collector;
A primary cooling circuit, the primary cooling circuit comprising:
The liquid cooling liquid storage tank is used for storing the secondary refrigerant;
the liquid cooling pump is communicated with the liquid cooling liquid storage tank and is used for extracting the secondary refrigerant;
The heating equipment is respectively communicated with the liquid cooling pump and the heat collector and is used for heating the secondary refrigerant and transmitting the heated secondary refrigerant to the heat collector; the heat collector is used for heating the refrigerant liquid by utilizing part of heat in the heated secondary refrigerant and transmitting the secondary refrigerant carrying the rest part of heat to the liquid cooling radiator;
the air outlet end of the liquid cooling radiator is communicated with the liquid cooling liquid storage tank, the air inlet end of the liquid cooling radiator is communicated with the heat collector and is used for cooling the secondary refrigerant carrying the rest heat and transmitting the cooled secondary refrigerant to the liquid cooling liquid storage tank;
A pump drive circuit, the pump drive circuit comprising:
the refrigerant liquid storage tank is used for storing a refrigerant;
the refrigerant pump is respectively communicated with the refrigerant liquid storage tank and the heat collector and is used for extracting the refrigerant liquid from the refrigerant and transmitting the refrigerant liquid to the heat collector;
The air inlet end of the expander is communicated with the heat collector and is used for receiving the refrigerant gas formed by heating the refrigerant liquid by the heat collector to expand so as to obtain expanded gas;
the electricity storage equipment is communicated with the air outlet end of the expander and is used for performing expansion work according to the expansion gas to obtain and store electric energy;
The first valve is connected in parallel to the energy storage pipeline which is communicated with the air outlet end of the expander and is used for controlling the turn-off of the energy storage pipeline;
the second valve is arranged on the energy storage pipeline which is communicated with the air inlet end of the expander and used for controlling the turn-off of the energy storage pipeline;
The heating device is arranged in the aircraft cabin, is communicated with the air outlet end of the expander and is used for heating the aircraft cabin by the refrigerant gas which passes through the first valve and carries all heat or the refrigerant gas which passes through the expander and carries the residual heat after being expanded to obtain refrigerant liquid;
the fourth valve is communicated in parallel with a heating pipeline of which the air outlet end is communicated with the heating equipment and is used for controlling the turn-off of the heating pipeline;
the third valve is arranged on a heating pipeline which is communicated with the air outlet end of the expander through the heating equipment and is used for controlling the turn-off of the heating pipeline;
The air inlet end of the second condenser is communicated with the fourth valve and the heating equipment, and the air outlet end of the second condenser is communicated with the refrigerant liquid storage tank and is used for carrying out condensation heat release on the refrigerant gas flowing through the fourth valve to obtain refrigerant liquid or enabling the refrigerant liquid obtained from the heating equipment to flow back into the refrigerant liquid storage tank.
2. The on-board pump drive energy utilization system of claim 1, wherein the electrical storage device comprises:
a generator which is communicated with the expander and is used for generating electricity by the gas expanded by the expander;
and the storage battery is connected with the generator and used for storing the power generated by the generator.
3. The on-board pump drive energy utilization system of claim 1, wherein the heating apparatus comprises:
the first condenser is respectively connected with the third valve and the air inlet end of the second condenser and is used for condensing and releasing heat of refrigerant gas carrying residual heat after the expansion of the expander;
And the fan is positioned at one side of the first condenser and used for transmitting heat discharged by condensation of the first condenser to all parts of the cabin.
4. The on-board pump drive energy utilization system of claim 1, wherein the heat generating device comprises: the heating elements are communicated in parallel between the liquid cooling pump and the heat collector.
5. The on-board pump drive energy utilization system of claim 4, wherein the heat generating device further comprises: and each equipment flowmeter is respectively arranged between the heating element and the liquid cooling pump.
6. The on-board pump drive energy utilization system of claim 1, wherein the main cooling circuit further comprises:
The first bypass valve is arranged on a bypass pipeline which is connected in parallel and communicated with the air outlet end of the liquid cooling radiator and the air inlet end of the second condenser and used for controlling the on-off of the bypass pipeline.
7. The on-board pump drive energy utilization system of claim 6, wherein the main cooling circuit further comprises:
A bypass flow meter disposed on the bypass conduit for measuring flow through the bypass conduit;
an eleventh temperature and pressure sensor is disposed on the bypass conduit for measuring temperature and pressure through the bypass conduit.
8. The on-board pump drive energy utilization system of claim 1, wherein the primary cooling circuit further comprises:
the liquid cooling flowmeter is arranged between the liquid cooling pump and the equipment flowmeter and is used for measuring the flow of the secondary refrigerant;
and a sixth temperature and pressure sensor, disposed between the liquid cooling pump and the equipment flow meter, for measuring the temperature and pressure of the coolant.
9. The on-board pump drive energy utilization system of claim 1, wherein the pump drive circuit further comprises:
The second bypass valve is arranged on a heat dissipation pipeline communicated with the air outlet end of the second condenser and the air inlet end of the liquid cooling radiator and used for controlling the on-off of the heat dissipation pipeline.
10. The on-board pump drive energy utilization system of claim 9, wherein the pump drive circuit further comprises:
And a twelfth temperature and pressure sensor provided on the heat dissipation pipe for measuring the temperature and pressure flowing through the heat dissipation pipe.
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