CN116534263B - Aircraft step heat dissipation device and control method - Google Patents
Aircraft step heat dissipation device and control method Download PDFInfo
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- CN116534263B CN116534263B CN202310806344.0A CN202310806344A CN116534263B CN 116534263 B CN116534263 B CN 116534263B CN 202310806344 A CN202310806344 A CN 202310806344A CN 116534263 B CN116534263 B CN 116534263B
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- regulating valve
- temperature
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- 230000017525 heat dissipation Effects 0.000 title claims abstract description 174
- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000000446 fuel Substances 0.000 claims abstract description 152
- 230000001105 regulatory effect Effects 0.000 claims description 130
- 239000003921 oil Substances 0.000 claims description 111
- 239000000523 sample Substances 0.000 claims description 96
- 239000010687 lubricating oil Substances 0.000 claims description 86
- 239000010720 hydraulic oil Substances 0.000 claims description 67
- 239000000295 fuel oil Substances 0.000 claims description 42
- 230000001276 controlling effect Effects 0.000 claims description 18
- 238000004891 communication Methods 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 230000005855 radiation Effects 0.000 abstract description 5
- 239000002826 coolant Substances 0.000 description 8
- 239000000314 lubricant Substances 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 238000007726 management method Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000694 effects Effects 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
-
- 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
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The invention relates to the technical field of aircraft thermal management, in particular to an aircraft cascade heat dissipation device and a control method. The aircraft step heat dissipation device comprises an oil supply device, a first heat dissipation device, a second heat dissipation device, an engine, an auxiliary oil supply device, a hot oil return device and a first one-way valve; an oil outlet of the oil supply device is communicated with the first end of the first heat dissipation device and the first end of the auxiliary oil supply device; the oil return port of the oil supply device is communicated with the first end of the hot oil return device; the second end of the first heat dissipating device is communicated with the second end of the hot oil return device and is also communicated with the first end of the second heat dissipating device through a first one-way valve; the second end of the auxiliary oil supply device is communicated with the first end of the second heat dissipation device; the first check valve prevents fuel in the second heat sink and the auxiliary fuel supply from flowing into the first heat sink. Therefore, the problem that the engine is abnormally operated due to overheat of fuel entering the engine through the heat radiation system when the engine is in overload operation is solved.
Description
Technical Field
The invention relates to the technical field of aircraft thermal management, in particular to an aircraft cascade heat dissipation device and a control method.
Background
Ultra-high speed aircraft use scramjet engines as propulsion systems, the flight speed often reaches above 4Ma, the engine generates heat and severe aerodynamic heating brings great thermal load to the aircraft, at which time traditional aircraft cooling methods using ram air are no longer applicable, and new thermal management approaches must be sought, where fuel oil as the combustible coolant is considered the best way to solve the thermal management problem.
At present, the heat load of the aircraft is mainly concentrated on the heat load of electronic equipment, hydraulic oil, lubricating oil and an engine, and the working environment temperature and the heat load are different due to different working characteristics, so that in order to more fully and efficiently utilize a fuel heat sink, the fuel is required to take away the heat load of the electronic equipment, the lubricating oil, the hydraulic oil and the engine according to a certain flow path and a certain control method instead of a certain fixed flow sequence and flow. In addition, in some specific stages, under the condition of overload operation of the engine, the temperature of the engine is increased, other equipment can also operate under high load, and after heat of electronic equipment, hydraulic oil and lubricating oil is taken away by fuel oil, the fuel oil with further increased temperature enters the engine, so that the normal operation and the service life of the engine can be influenced.
Disclosure of Invention
The invention provides an aircraft step heat dissipation device and a control method, which aim to solve the problem that when an engine is in overload operation, fuel oil enters the engine through a heat dissipation system to overheat so that the engine is in abnormal operation.
In a first aspect, the present invention provides an aircraft step heat sink comprising:
the device comprises an oil supply device, a first heat dissipation device, a second heat dissipation device, an engine, an auxiliary oil supply device, a hot oil return device and a first one-way valve;
an oil outlet of the oil supply device is communicated with the first end of the first heat dissipation device; an oil outlet of the oil supply device is communicated with a first end of the auxiliary oil supply device; the oil return port of the oil supply device is communicated with the first end of the hot oil return device;
the second end of the first heat radiating device is communicated with the second end of the hot oil return device; the second end of the first heat dissipation device is communicated with the first end of the second heat dissipation device through the first one-way valve;
the second end of the auxiliary oil supply device is communicated with the first end of the second heat dissipation device;
the first one-way valve prevents fuel oil in the second heat dissipating device and the auxiliary fuel supply device from flowing into the first heat dissipating device; the second end of the second heat sink is in communication with the engine.
In some embodiments, the second heat sink comprises a second temperature probe; the second temperature probe is arranged at the second end of the second heat dissipation device, and the temperature of the fuel oil flowing out of the second end of the second heat dissipation device is obtained; the auxiliary oil supply device comprises a second flow regulating valve; the second temperature probe is electrically connected with the second flow regulating valve.
In some embodiments, the first heat sink comprises a first temperature probe; the first temperature probe is arranged at the second end of the first heat dissipation device, and the temperature of fuel oil flowing out of the second end of the first heat dissipation device is obtained; the hot oil return device comprises a first flow regulating valve; the first temperature probe is electrically connected with the first flow regulating valve.
In some embodiments, the first heat dissipating device further comprises an electronic device heat dissipating part, a lubricating oil heat dissipating part, and a hydraulic oil heat dissipating part; an oil outlet of the oil supply device is communicated with a first end of the electronic equipment radiating part; the second end of the electronic equipment heat dissipation part is communicated with the first end of the lubricating oil heat dissipation part; the second end of the electronic equipment heat dissipation part is communicated with the first end of the hydraulic oil heat dissipation part; the second end of the lubricating oil heat dissipation part is communicated with the second end of the hydraulic oil heat dissipation part and forms the second end of the first heat dissipation device.
In some embodiments, the electronic device heat sink includes an electronic device heat sink, a third flow regulating valve, a third temperature probe; an oil outlet of the oil supply device is communicated with the first end of the third flow regulating valve; the second end of the third flow regulating valve is communicated with the first end of the radiator of the electronic equipment; the second end of the electronic equipment radiator is set as the second end of the electronic equipment radiating part; the third temperature probe is arranged at the second end of the radiator of the electronic equipment, and the temperature of the fuel oil flowing out of the second end of the radiator of the electronic equipment is obtained.
In some embodiments, the lubricating oil heat dissipation part comprises a lubricating oil radiator, a fourth flow regulating valve, a second one-way valve and a fourth temperature probe; the fourth flow regulating valve, the second one-way valve and the lubricating oil radiator are sequentially communicated; one end of the fourth flow regulating valve, which is far away from the second one-way valve, is arranged as a first end of the lubricating oil heat dissipation part; one end of the lubricating oil radiator, which is far away from the second one-way valve, is arranged as a second end of the lubricating oil radiating part; the second one-way valve prevents fuel in the lubricating oil radiator from flowing to the fourth flow regulating valve; the fourth temperature probe is arranged at the second end of the lubricating oil heat dissipation part, and the temperature of the fuel oil flowing out of the second end of the lubricating oil heat dissipation part is obtained.
In some embodiments, the first heat sink further comprises a sixth flow regulating valve; the first end of the sixth flow regulating valve is communicated with an oil outlet of the oil supply device; the second end of the sixth flow regulating valve is communicated with one end, close to the second one-way valve, of the lubricating oil heat dissipation part.
In some embodiments, the hydraulic oil heat sink includes a hydraulic oil radiator, a fifth flow regulating valve, a fifth temperature probe; the first end of the fifth flow regulating valve is communicated with the second end of the electronic equipment radiating part; the second end of the fifth flow regulating valve is communicated with the first end of the hydraulic oil radiator; the second end of the hydraulic oil radiator is set as the second end of the hydraulic oil radiating part; the fifth temperature probe is arranged at the second end of the hydraulic oil heat dissipation part, and the temperature of the fuel oil flowing out of the second end of the hydraulic oil heat dissipation part is obtained.
In a second aspect, the present invention further provides a method for controlling heat dissipation of an aircraft step, where the method includes:
step S11, based on the starting of the aircraft, the fuel oil supplied by the fuel oil supply device sequentially passes through the first heat dissipation device and the second heat dissipation device and enters the engine for combustion;
step S12, controlling the opening of a second flow regulating valve based on the fact that the temperature T2 acquired by the second temperature probe is larger than a second temperature threshold;
step S13, based on the second flow regulating valve being opened and the temperature T1 acquired by the first temperature probe being greater than a first temperature threshold, the first flow regulating valve is opened; wherein the second flow regulating valve opening is larger than the first flow regulating valve opening.
In some embodiments, the control method further comprises:
and step S14, controlling the second flow regulating valve to be opened and controlling the first flow regulating valve to be closed based on the fact that the temperature T2 acquired by the second temperature probe is smaller than or equal to the second temperature threshold and larger than a third temperature threshold.
In some embodiments, the control method further comprises:
and step S15, based on the fact that the temperature T2 acquired by the second temperature probe is smaller than or equal to a third temperature threshold, closing a second flow regulating valve, and controlling the first flow regulating valve to be closed.
In some embodiments, the control method further comprises:
step S16, controlling the opening of the third flow regulating valve to be increased based on the fact that the temperature T3 acquired by the third temperature probe is larger than the first temperature threshold;
step S17, controlling the opening of the sixth flow regulating valve to be increased based on the fact that the temperature T4 acquired by the fourth temperature probe is larger than the first temperature threshold;
and S18, controlling the opening of the fifth flow regulating valve to be increased based on the fact that the temperature T5 acquired by the fifth temperature probe is greater than the first temperature threshold.
In order to solve the problem that the engine is abnormally operated due to overheat of fuel entering the engine through a heat radiation system when the engine is in overload operation, the invention has the following advantages:
1. the aircraft step heat dissipation device is provided with two fuel oil heat dissipation loops, wherein the first loop is that fuel oil sequentially flows through the first heat dissipation device and the hot oil return device from the oil supply device and finally returns to the inside of the oil supply device; the second loop is that the fuel oil flows through the auxiliary fuel supply device and the second heat dissipation device in sequence from the fuel supply device and finally enters the engine; a first one-way valve is arranged between the two loops, and fuel oil of the first loop and fuel oil of the second loop can be separated by the first one-way valve, so that high-temperature fuel oil of the first loop can be prevented from flowing to the engine, and abnormal operation of the engine is caused. And meanwhile, under the condition that the normal operation of the engine is not influenced, the first loop fuel oil cools the on-board heating component through the first heat radiating device.
2. Under certain special flight conditions (such as large maneuvering, forced flight and the like), the real-time dynamic adjustment of the inlet fuel temperature of the second heat dissipation device can be realized through the adjustment of the auxiliary oil supply device and the hot oil return device, and the heat load of the engine is effectively taken away, so that the safe and reliable operation of the engine is ensured.
Drawings
FIG. 1 illustrates a schematic view of an aircraft step heat sink of an embodiment;
FIG. 2 illustrates a schematic diagram of an aircraft step heat dissipation control method of an embodiment;
fig. 3 shows a schematic diagram of an aircraft step heat dissipation control method of another embodiment.
Reference numerals:
10 an oil supply device; an 11 oil tank; 12 oil feed pumps; 13 a third one-way valve; 20 a first heat sink; a first temperature probe 21; 22 a heat sink portion of the electronic device; 221 an electronic device heat sink; 222 a third flow regulating valve; 223 third temperature probe; 23 lubricating oil heat dissipation parts; 231 a second one-way valve; 232 a fourth flow regulating valve; 233 a fourth temperature probe; 234 a lubricating oil radiator; 24 hydraulic oil heat dissipation parts; 241 hydraulic oil radiator; 242 a fifth flow regulating valve; 243 a fifth temperature probe; 25 on-board electronic devices; 26 a lubricating oil circulation device; 27 oil pressure equipment; 28 a sixth flow regulating valve; a second heat sink 30; a second temperature probe 31; 32 a second heat sink; 33 a first coolant supply; a 40 engine; 50 auxiliary oil supply means; a second flow regulating valve 51; 60 hot oil return means; 61 a first flow regulating valve; 62 return oil radiator; 63 a sixth temperature probe; a second coolant supply 64; 70 a first one-way valve; 80 booster pump.
Detailed Description
The disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those of ordinary skill in the art to better understand and thus practice the present disclosure, and are not meant to imply any limitation on the scope of the present disclosure.
As used herein, the term "comprising" and variants thereof are to be interpreted as meaning "including but not limited to" open-ended terms. The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment. The term "another embodiment" is to be interpreted as "at least one other embodiment".
The embodiment discloses an aircraft step heat abstractor, as shown in fig. 1, may include:
the engine comprises an oil supply device 10, a first heat dissipation device 20, a second heat dissipation device 30, an engine 40, an auxiliary oil supply device 50, a hot oil return device 60 and a first check valve 70;
the oil outlet of the oil supply device 10 is communicated with the first end of the first heat radiating device 20; the oil outlet of the oil supply device 10 is communicated with the first end of the auxiliary oil supply device 50; the oil return port of the oil supply device 10 is communicated with the first end of the hot oil return device 60;
a second end of the first heat sink 20 communicates with a second end of the hot oil return 60; the second end of the first heat sink 20 communicates with the first end of the second heat sink 30 through a first one-way valve 70;
the second end of the auxiliary oil supply 50 communicates with the first end of the second heat sink 30;
the first check valve 70 prevents the fuel in the second heat sink 30 and the auxiliary fuel supply 50 from flowing into the first heat sink 20; a second end of the second heat sink 30 communicates with the engine 40.
In this embodiment, various components on the ultra-high speed aircraft may generate heat during flight. In order to ensure the flight safety of the aircraft, the heat-generating components can be subjected to heat dissipation treatment. As shown in fig. 1, the aircraft step heat sink may include an oil supply 10, a first heat sink 20, a second heat sink 30, an engine 40, an auxiliary oil supply 50, a hot oil return 60, and a first check valve 70. The fuel supply apparatus 10 is configured to supply fuel and may include a plurality of fuel outlets and a plurality of fuel return ports. The first heat dissipating device 20 is configured to dissipate heat from the functional component using fuel while the other functional component is operating, and the first heat dissipating device 20 may include a first end and a second end. Wherein at least one oil outlet of the oil supply device 10 is communicated with the first end of the first heat dissipating device 20, so that fuel flows into the first heat dissipating device 20, thereby taking away heat transferred by the functional components. The hot oil return device 60 may be configured to recover the high temperature fuel exiting the first radiator 20, and the hot oil return device 60 may include a first end and a second end. The second end of the first heat dissipating device 20 is communicated with the second end of the hot oil return device 60, and the fuel oil flowing through the first heat dissipating device 20 absorbs heat and can flow to the hot oil return device 60 for recovery. At least one return port of the fuel supply 10 communicates with a first end of the hot oil return 60 so that the recovered fuel may be stored in the fuel supply 10. The auxiliary fuel supply 50 is for delivering fuel and may include a first end and a second end. At least one outlet of the fuel supply 10 communicates with a first end of the auxiliary fuel supply 50 to allow fuel to flow into the auxiliary fuel supply 50. The second heat sink 30 is used to dissipate heat from a housing of the engine 40 in operation and may include a first end and a second end. The second end of the auxiliary oil supply device 50 is communicated with the first end of the second heat dissipation device 30, and the second end of the second heat dissipation device 30 is communicated with the engine 40, so that fuel flowing through the auxiliary oil supply device 50 flows into the second heat dissipation device 30 to absorb heat transferred by the shell when the engine 40 works, and therefore the shell of the engine 40 can be cooled, and the service life of the engine 40 is prolonged. At the same time, the fuel oil absorbing heat finally enters the engine 40 to burn better, and power the engine 40. The second end of the first heat sink 20 and the first end of the second heat sink 30 may communicate through a first check valve 70. When the engine 40 is operated at a high load, the temperature of the housing of the engine 40 increases, and a low-temperature fuel is required for heat dissipation treatment, and at the same time, other functional components may be operated at a high load, and the temperature of the fuel flowing through the first heat sink 20 to absorb heat transferred from the functional components increases. The fuel flowing through the first heat sink 20 is delivered into the second heat sink 30, so that the cooling effect of the fuel on the housing of the engine 40 is reduced, which is not beneficial to the normal operation of the engine 40. Because of the complex piping in the first heat sink 20, the pressure drop is greater for the fuel flowing through the first heat sink 20 and the piping of the auxiliary fuel supply 50 is simple, the pressure drop is less for the fuel flowing through the auxiliary fuel supply 50, resulting in the fuel pressure exiting the first heat sink 20 being less than the fuel pressure exiting the auxiliary fuel supply 50. The first check valve 70 blocks the fuel flowing out of the first heat sink 20 from flowing to the second heat sink 30, and the fuel flowing out of the auxiliary fuel supply device 50 is blocked from flowing to the first heat sink 20 by the first check valve 70. The fuel oil flowing out of the auxiliary fuel supply device 50 flows into the second heat radiating device 30 to perform heat radiation treatment on the shell of the engine 40, so that the normal operation of the engine 40 is ensured.
In other embodiments, as shown in fig. 1, the oil supply device 10 may include an oil tank 11, an oil supply pump 12, and a third check valve 13. The tank 11 may be used to store fuel for providing fuel for the engine 40. The fuel supply pump 12 may include a first end and a second end for drawing fuel. The outlet of the tank 11 communicates with a first end of the feed pump 12 to pump the desired fuel. The third one-way valve 13 may include a first end and a second end. The second end of the fuel feed pump 12 is communicated with the first end of the third one-way valve 13, and the second end of the third one-way valve 13 is communicated with the first end of the first heat dissipating device 20, so that fuel flows into the first heat dissipating device 20, and heat transferred during the operation of the functional equipment is taken away. The second end of the third check valve 13 may also be in communication with the first end of the auxiliary fuel supply 50, so that fuel flows into the auxiliary fuel supply 50 and is delivered to the second heat sink 30 to remove heat transferred from the housing of the engine 40. The return port of the tank 11 communicates with the first end of the hot oil return means 60 to return the warmer fuel in the first radiator means 20 to the tank 11 for storage.
In some embodiments, as shown in fig. 1, the second heat sink 30 includes a second temperature probe 31; the second temperature probe 31 is arranged at the second end of the second heat dissipation device 30, and obtains the temperature of the fuel oil flowing out of the second end of the second heat dissipation device 30; the auxiliary oil supply device 50 includes a second flow regulating valve 51; the second temperature probe 31 is electrically connected to a second throttle valve 51.
In the present embodiment, as shown in fig. 1, the second heat sink 30 may include a second temperature probe 31. A second temperature probe 31 may be provided at a second end of the second heat sink 30 for detecting the temperature of the fuel flowing out of the second end of the second heat sink 30. The auxiliary fuel supply 50 may include a second flow regulating valve 51 for regulating the delivery state of the fuel to the second radiator 30. The second temperature probe 31 can be electrically connected with the second flow regulating valve 51, when the second temperature probe 31 detects that the temperature of the fuel flowing out of the second end of the second heat dissipating device 30 is greater than a set threshold (i.e. the temperature of the fuel is too high), the opening of the second flow regulating valve 51 can be controlled to increase, so that the amount of the low-temperature fuel flowing through the auxiliary fuel supply device 50 is increased, the heat dissipating treatment of the housing of the engine 40 is facilitated, and the engine 40 is enabled to operate normally.
In other embodiments, as shown in fig. 1, the pipeline of the auxiliary fuel supply device 50 is long, and the pressure drop generated by the fuel flowing through the auxiliary fuel supply device may lead to insufficient pressure of the fuel delivered to the second heat dissipation device 30, so that two ends of the pressurizing pump 80 are respectively communicated with the auxiliary fuel supply device 50 and the second heat dissipation device 30, and the delivery pressure of the fuel is enhanced.
In other embodiments, as shown in fig. 1, the second heat dissipating device 30 may further include a first heat dissipating agent supply 33, a second heat sink 32. The first coolant supply unit 33 transfers heat from the casing of the engine 40 to the second radiator 32, so that the fuel flowing through the second radiator 32 dissipates heat from the casing of the engine 40, and the service life of the engine 40 is prolonged.
In some embodiments, as shown in fig. 1, the first heat sink 20 includes a first temperature probe 21; the first temperature probe 21 is arranged at the second end of the first heat dissipation device 20 and is used for acquiring the temperature of fuel oil flowing out of the second end of the first heat dissipation device 20; the hot oil return means 60 comprises a first flow regulating valve 61; the first temperature probe 21 is electrically connected to the first throttle valve 61.
In this embodiment, as shown in fig. 1, the first heat dissipating device 20 may include a first temperature probe 21, where the first temperature probe 21 is disposed at a second end of the first heat dissipating device 20, for detecting a temperature of fuel flowing out of the second end of the first heat dissipating device 20. The thermal oil return apparatus 60 may include a first throttle valve 61 for adjusting the fuel delivery status into the thermal oil return apparatus 60. The first temperature probe 21 is electrically connected with the first flow regulating valve 61, when the first temperature probe 21 detects that the temperature of the fuel flowing out of the second end of the first heat dissipating device 20 is greater than a set threshold (i.e. the temperature of the fuel is too high), the opening of the first flow regulating valve 61 can be controlled, so that the fuel flows into the hot oil return device 60, and the high-temperature fuel is recovered into the oil supply device 10.
In other embodiments, as shown in FIG. 1, the hot oil return apparatus 60 may further include a return radiator 62, a sixth temperature probe 63, and a second coolant supply 64. The first flow control valve 61, the return radiator 62, and the sixth temperature probe 63 are sequentially connected, and the second coolant supply unit 64 is connected to the return radiator 62. When the high-temperature fuel flowing into the first throttle valve 61 flows to the return radiator 62, the second heat radiation supply portion radiates heat from the fuel flowing into the return radiator 62, and the sixth temperature probe 63 detects the temperature of the fuel flowing out of the return radiator 62. When the sixth temperature probe 63 detects that the fuel temperature is greater than the set threshold, the sixth temperature probe 63 controls the second coolant supply portion 64 to increase the supply amount of coolant, thereby reducing the temperature of the fuel flowing through the oil-return radiator 62. The fuel oil subjected to the heat recovery and radiation treatment by the hot oil return device 60 flows out of the hot oil return device 60 and then flows into the oil supply device 10 for storage.
In some embodiments, as shown in fig. 1, the first heat dissipating device 20 further includes an electronic device heat dissipating portion 22, a lubricating oil heat dissipating portion 23, and a hydraulic oil heat dissipating portion 24; the oil outlet of the oil supply device 10 is communicated with the first end of the electronic equipment heat dissipation part 22; the second end of the electronic device heat dissipation part 22 is communicated with the first end of the lubricating oil heat dissipation part 23; the second end of the electronic device heat dissipation part 22 is communicated with the first end of the hydraulic oil heat dissipation part 24; a second end of the oil radiator 23 communicates with a second end of the hydraulic oil radiator 24 and forms a second end of the first radiator 20.
In this embodiment, as shown in fig. 1, the first heat dissipating device 20 may further include an electronic device heat dissipating part 22, a lubricating oil heat dissipating part 23, and a hydraulic oil heat dissipating part 24; the electronic device heat dissipation part 22 is used for performing heat dissipation treatment on the electronic device, and may include a first end and a second end. At least one oil outlet of the oil supply device 10 is communicated with the first end of the electronic equipment heat dissipation part 22, and fuel oil flows in from the first end of the electronic equipment heat dissipation part 22 to take away heat transferred by the electronic equipment during operation. The lubricating oil heat dissipating part 23 is used for heat dissipating treatment of the lubricating oil device, and may include a first end and a second end. The second end of the electronic equipment heat dissipation part 22 is communicated with the first end of the lubricating oil heat dissipation part 23, and the fuel oil flowing out of the second end of the electronic equipment heat dissipation part 22 flows in from the first end of the lubricating oil heat dissipation part 23 to take away the heat transferred by the lubricating oil equipment during operation. The hydraulic oil heat dissipation portion 24 is used for performing heat dissipation treatment on hydraulic oil equipment, and may include a first end and a second end. The second end of the electronic equipment heat dissipation part 22 is communicated with the first end of the hydraulic oil heat dissipation part 24, and the fuel oil flowing out of the second end of the electronic equipment heat dissipation part 22 flows in from the first end of the hydraulic oil heat dissipation part 24 to take away heat transferred by the hydraulic oil equipment during operation. The second end of the lubricating oil heat dissipation part 23 is communicated with the second end of the hydraulic oil heat dissipation part 24 and forms the second end of the first heat dissipation device 20, so that fuel oil which transfers heat when the functional equipment is taken away can flow out of the second end of the first heat dissipation device 20 together, and the heat dissipation treatment work of the related functional equipment is completed.
In other embodiments, as shown in fig. 1, the fuel supplied from the fuel supply device 10 flows through the electronic device heat dissipation portion 22, the lubricating oil heat dissipation portion 23, and the hydraulic oil heat dissipation portion 24 to perform heat dissipation treatment on the on-board electronic device 25, the lubricating oil circulation device 26, and the hydraulic oil device 27 in this order. Because the on-board electronic device 25 is operated with less heat transferred, the heat transferred by the fuel oil absorption raises the temperature of the fuel oil to be lower, and the heat dissipation treatment can be carried out on the lubricating oil circulation device 26 and the oil pressure device 27. Meanwhile, the on-board electronic device 25 is an important functional component, and if the on-board electronic device 25 fails due to untimely cooling, the operation of the engine 40 is seriously affected, so that fuel is allowed to flow into the electronic device heat dissipation part 22 preferentially to perform heat dissipation treatment on the on-board electronic device 25. The fuel flowing out of the electronic device heat dissipation part 22 flows into the lubricating oil heat dissipation part 23 and the hydraulic oil heat dissipation part 24, respectively.
In some embodiments, as shown in fig. 1, the electronic device heat sink 22 includes an electronic device heat sink 221, a third flow regulating valve 222, and a third temperature probe 223; an oil outlet of the oil supply device 10 is communicated with a first end of a third flow regulating valve 222; a second end of the third flow regulating valve 222 is communicated with a first end of the electronic equipment radiator 221; a second end of the electronic device heat sink 221 is provided as a second end of the electronic device heat sink 22; the third temperature probe 223 is disposed at the second end of the electronic device heat sink 221, and obtains the temperature of the fuel flowing out from the second end of the electronic device heat sink 221.
In this embodiment, as shown in fig. 1, the electronic device heat dissipating part 22 may include an electronic device heat sink 221, a third flow regulating valve 222, and a third temperature probe 223. The electronic device heat sink 221 is used for transferring heat during operation of the electronic device and performing heat dissipation treatment, and may include a first end and a second end. The third flow regulating valve 222 is used to regulate the fuel delivery into the electronic device heat sink 22 and may include a first end and a second end. At least one oil outlet of the oil supply device 10 is communicated with the first end of the third flow regulating valve 222, the second end of the third flow regulating valve 222 is communicated with the first end of the electronic equipment radiator 221, so that fuel flows through the third flow regulating valve 222 to flow into the electronic equipment radiator 221, and heat transferred to the electronic equipment radiator 221 during operation of the electronic equipment is taken away. A second end of the electronic device heat sink 221 is configured as a second end of the electronic device heat sink 22, so that fuel that transfers heat when the electronic device is operating is discharged. The third temperature probe 223 is disposed at the second end of the electronic device heat sink 221, and can detect the temperature of the fuel flowing out of the second end of the electronic device heat sink 221, and adjust other functional devices according to the detection result.
In some embodiments, as shown in fig. 1, the lubricating oil heat sink 23 includes a lubricating oil radiator 234, a fourth flow regulating valve 232, a second check valve 231, a fourth temperature probe 233; the fourth flow regulating valve 232, the second one-way valve 231 and the lubricating oil radiator 234 are communicated in sequence; one end of the fourth flow regulating valve 232, which is far away from the second one-way valve 231, is set as a first end of the lubricating oil heat dissipation part 23; one end of the lubricating oil radiator 234 remote from the second check valve 231 is provided as a second end of the lubricating oil radiator 23; the second check valve 231 prevents fuel in the lubricating oil radiator 234 from flowing to the fourth flow regulating valve 232; the fourth temperature probe 233 is disposed at the second end of the lubricant heat dissipation part 23, and obtains the temperature of the fuel flowing out from the second end of the lubricant heat dissipation part 23.
In this embodiment, as shown in fig. 1, the lubricating oil heat dissipating part 23 may include a lubricating oil radiator 234, a fourth flow regulating valve 232, a second check valve 231, and a fourth temperature probe 233. The lubricating oil radiator 234 is used for transferring heat and performing heat dissipation treatment during operation of the lubricating oil equipment, and may include a first end and a second end. The fourth flow regulating valve 232 is used to regulate the fuel delivery into the lubricating oil radiator 23, and may include a first end and a second end. The first end of the fourth flow regulating valve 232 is set as the first end of the lubricating oil heat dissipating part 23, and the lubricating oil is caused to flow into the lubricating oil heat dissipating part 23 to dissipate heat from the lubricating oil radiator 234. A second check valve 231 is disposed between the second end of the fourth flow regulating valve 232 and the first end of the lubricating oil radiator 234 for communication, and the second check valve 231 can prevent the fuel flowing into the lubricating oil radiator 234 from flowing to the fourth flow regulating valve 232. The second end of the lubricating oil radiator 234 is set as the second end of the lubricating oil radiator 23, so that the fuel oil carrying away the heat transferred during the operation of the lubricating oil apparatus can flow out of the second end of the lubricating oil radiator 23. The fourth temperature probe 233 is provided at the second end of the lubricant heat dissipation part 23, and can detect the temperature of the fuel flowing out of the second end of the lubricant heat dissipation part 23, and adjust other functional devices according to the detection result.
In some embodiments, as shown in fig. 1, the first heat sink 20 further includes a sixth flow regulating valve 28; a first end of the sixth flow regulating valve 28 is communicated with an oil outlet of the oil supply device 10; a second end of the sixth flow regulating valve 28 communicates with an end of the lubricating oil heat dissipating portion 23 near the second check valve 231.
In this embodiment, as shown in fig. 1, the first heat dissipating device 20 may further include a sixth flow regulating valve 28. The sixth flow regulating valve 28 is used to regulate the fuel delivery into the lubricating oil radiator 23 and may include a first end and a second end. The first end of the sixth throttle valve 28 communicates with at least one outlet of the oil supply device 10 so that fuel can flow into the lubricating oil radiator 23. The second end of the sixth flow regulating valve 28 is communicated with one end of the second one-way valve 231 close to the lubricating oil heat dissipation part 23, when other functional components are in high-load operation, the important grade of the lubricating oil heat dissipation part 23 is higher than that of the hydraulic oil heat dissipation part 24, if the fuel oil flowing in from the fourth flow regulating valve 232 possibly absorbs heat transferred by other functional components to cause the fuel oil temperature to be higher than a set threshold, effective heat dissipation treatment cannot be provided for lubricating oil equipment, and the functional components possibly wear, so that the service life of the lubricated device is affected. At this time, the opening of the sixth flow regulating valve 28 is controlled, and the low-temperature fuel provided by the fuel supply device 10 flows into the lubricating oil heat dissipation part 23 from the second end of the sixth flow regulating valve 28, so that the lubricating oil heat dissipation part 23 can be effectively subjected to heat dissipation treatment, thereby ensuring the normal heat dissipation treatment work of the first heat dissipation device 20 on other functional components.
In some embodiments, as shown in fig. 1, the hydraulic oil heat sink 24 includes a hydraulic oil radiator 241, a fifth throttle valve 242, a fifth temperature probe 243; a first end of the fifth flow regulating valve 242 is communicated with a second end of the electronic device heat dissipating part 22; a second end of the fifth flow regulating valve 242 is communicated with a first end of the hydraulic oil radiator 241; a second end of the hydraulic oil radiator 241 is provided as a second end of the hydraulic oil heat radiating portion 24; the fifth temperature probe 243 is disposed at the second end of the hydraulic oil heat dissipation portion 24, and obtains the temperature of the fuel flowing out from the second end of the hydraulic oil heat dissipation portion 24.
In the present embodiment, as shown in fig. 1, the hydraulic oil heat dissipating portion 24 may include a hydraulic oil radiator 241, a fifth flow regulating valve 242, and a fifth temperature probe 243. The fifth flow regulator valve 242 is used to regulate the fuel delivery into the hydraulic oil sink portion 24 and may include a first end and a second end. The first end of the fifth flow regulating valve 242 is communicated with the second end of the electronic device heat dissipating part 22, so that the fuel flows into the hydraulic oil heat dissipating part 24 to take away the heat transferred by the hydraulic oil device during operation. The hydraulic oil radiator 241 is used for transferring heat and performing heat dissipation treatment when the hydraulic oil device is in operation, and may include a first end and a second end. The second end of the fifth flow regulating valve 242 is communicated with the first end of the hydraulic oil radiator 241, so that the fuel flows into the hydraulic oil radiator 241 to take away heat transferred by the hydraulic oil equipment during operation. The second end of the hydraulic oil radiator 241 is set as the second end of the hydraulic oil heat dissipation portion 24, and the fifth temperature probe 243 is set at the second end of the hydraulic oil heat dissipation portion 24, so as to detect the fuel temperature of the second end of the hydraulic oil heat dissipation portion 24, and adjust the operation of other functional devices according to the detection result.
In other embodiments, as shown in fig. 1, since the importance level of the lubricating oil circulation device 26 is higher than that of the oil pressure device 27, if the lubricating oil circulation device 26 is not capable of performing effective heat dissipation treatment during operation, wear of the functional device may be caused, and the service life of the lubricated device may be affected. The opening of the fourth flow regulating valve 232 can be controlled to be increased, and the opening of the fifth flow regulating valve 242 can be controlled to be reduced, so that the fuel flowing out of the electronic equipment radiating part 22 is split into the lubricating oil radiating part 23 and the hydraulic oil radiating part 24, and the fuel flowing into the lubricating oil radiating part 23 is more than the fuel flowing into the hydraulic oil radiating part 24, so that the normal operation of the lubricating oil circulating equipment 26 is ensured.
In some embodiments, as shown in fig. 2, the control method includes:
step S11, based on the starting of the aircraft, the fuel supply device 10 supplies fuel to the engine 40 for burning after sequentially passing through the first heat dissipation device 20 and the second heat dissipation device 30;
step S12, controlling the second flow regulating valve 51 to open based on the temperature T2 obtained by the second temperature probe 31 being greater than the second temperature threshold;
step S13, based on the second flow regulating valve 51 being opened and the temperature T1 obtained by the first temperature probe 21 being greater than the first temperature threshold, the first flow regulating valve 61 is opened; wherein the second flow regulating valve opening is larger than the first flow regulating valve opening.
In this embodiment, as shown in fig. 2, the control method may include steps S11 to S13, and the following describes the above steps in detail:
in step S11, when the aircraft is started, the fuel supply device 10 supplies fuel, the fuel firstly passes through the first heat dissipation device 20 to perform heat dissipation treatment on functional equipment in operation, takes away heat transferred during operation of the functional equipment, then passes through the second heat dissipation device 30 to perform heat dissipation treatment on the housing of the engine 40, takes away heat transferred by the housing of the engine 40, and finally can enter the engine 40 to burn, so that normal operation of the engine 40 is maintained.
In step S12, when the second temperature probe 31 detects that the temperature T2 of the fuel flowing out of the second heat dissipating device 30 is greater than the second temperature threshold (i.e. the high load operation of the engine 40 causes the high temperature state of the engine 40 housing), the second temperature probe 31 can control the second flow regulating valve 51 of the auxiliary fuel supply device 50 to open, so that the low temperature fuel flows into the second heat dissipating device 30, takes away the heat transferred by the engine 40 housing, finally enters the engine 40 for burning, and prolongs the service life of the engine 40.
In step S13, the fuel is supplied to the fuel supply device 10, and the second temperature probe 31 in the second heat sink 30 controls the second flow regulating valve 51 in the auxiliary fuel supply device 50 to open, so that the fuel flows into the auxiliary fuel supply device 50. When the fuel flows to the second heat dissipating device 30, the first temperature probe 21 detects that the temperature T1 of the fuel flowing out of the first heat dissipating device 20 is greater than the first temperature threshold, and the first temperature probe 21 controls the first flow regulating valve 61 to open, so that the fuel flowing out of the first heat dissipating device 20 flows to the hot oil return device 60, and finally enters the oil supply device 10 for storage and use. The opening of the second flow regulating valve 51 is larger than that of the first flow regulating valve 61, and the fuel pressure flowing out of the first heat dissipating device 20 is smaller than that flowing out of the auxiliary fuel supply device 50, so that the high-temperature fuel flowing out of the second end of the first heat dissipating device 20 can be prevented from flowing into the second heat dissipating device 30 through the first one-way valve 70, and the normal operation of the engine 40 is ensured.
In some embodiments, as shown in fig. 3, the control method further includes:
in step S14, the second flow regulating valve 51 is controlled to be opened and the first flow regulating valve 61 is controlled to be closed based on the temperature T2 obtained by the second temperature probe 31 being less than or equal to the second temperature threshold and greater than the third temperature threshold.
In this embodiment, as shown in fig. 3, the control method may further include step S14, when the fuel supply device 10 supplies fuel, the second temperature probe 31 detects that the temperature T2 of the fuel flowing out of the second heat dissipating device 30 is less than or equal to the second temperature threshold and is greater than the third temperature threshold (i.e. the medium load operation of the engine 40 causes the housing of the engine 40 to be in a higher temperature state), the second temperature probe 31 controls the second flow regulating valve 51 of the auxiliary fuel supply device 50 to open, the first temperature probe 21 of the first heat dissipating device 20 controls the first flow regulating valve 61 in the hot oil return device 60 to close, so that the fuel flowing out of the first heat dissipating device 20 flows into the first one-way valve 70 and flows into the second heat dissipating device 30 together with the fuel flowing out of the auxiliary fuel supply device 50, thereby not only taking away the heat transferred by the housing of the engine 40, but also improving the temperature of the fuel flowing into the engine 40 and improving the fuel combustion efficiency.
In some embodiments, as shown in fig. 3, the control method further includes:
in step S15, the second flow regulating valve 51 is closed and the first flow regulating valve 61 is controlled to be closed based on the temperature T2 obtained by the second temperature probe 31 being less than or equal to the third temperature threshold.
In this embodiment, as shown in fig. 3, the control method may further include step S15, when the fuel supply device 10 supplies fuel, the second temperature probe 31 detects that the temperature T2 of the fuel flowing out of the second heat dissipation portion is less than or equal to a third temperature threshold (i.e. the low load operation of the engine 40 causes the housing of the engine 40 to be in a lower temperature state), the second temperature probe 31 controls the second flow regulating valve 51 in the auxiliary fuel supply system to be closed, the first temperature probe 21 in the first heat dissipation device 20 controls the first flow regulating valve 61 in the hot oil return device 60 to be closed, so that the fuel flows through the first heat dissipation device 20 and the second heat dissipation device 30 in sequence, and takes away the heat transferred during the operation of the functional equipment and the heat transferred by the housing of the engine 40, and finally enters the engine 40 to burn, so as to maintain the normal operation of the engine 40.
In some embodiments, as shown in fig. 3, the control method further includes:
step S16, based on the temperature T3 acquired by the third temperature probe 223 being greater than the first temperature threshold, controlling the opening of the third flow regulating valve 222 to increase;
step S17, based on the temperature T4 acquired by the fourth temperature probe 233 being greater than the first temperature threshold, controlling the opening of the sixth throttle valve 28 to increase;
in step S18, the opening of the fifth throttle valve 242 is controlled to increase based on the temperature T5 obtained by the fifth temperature probe 243 being greater than the first temperature threshold.
In the present embodiment, as shown in fig. 3, the control method may further include steps S16 to S18. The above steps are described in detail below:
in step S16, when the aircraft is started, the third temperature probe 223 detects that the temperature T3 of the fuel flowing out of the heat dissipation portion 22 of the electronic device is greater than the first temperature threshold, and controls the opening of the third flow regulating valve 222 to increase, so that the amount of fuel flowing through the third flow regulating valve 222 from the fuel supply device 10 increases, and therefore, heat in the heat dissipation portion 22 of the electronic device can be rapidly taken away, so as to ensure normal operation of the electronic device.
In step S17, the fourth temperature probe 233 detects that the temperature T4 of the fuel flowing out of the lubricating oil heat dissipation portion 23 is greater than the first temperature threshold, and controls the opening of the sixth flow regulating valve 28 to increase, so that more low-temperature fuel flows into the lubricating oil heat dissipation portion 23, and heat in the lubricating oil heat dissipation portion 23 can be quickly taken away, so as to ensure normal operation of the lubricating oil equipment. In other embodiments, the opening of the sixth flow regulating valve 28 is controlled to be increased, and the opening of the fourth flow regulating valve 232 is controlled to be decreased, so that the higher temperature fuel flowing out of the heat dissipation portion 22 of the electronic device flows into the lubricating oil heat dissipation portion 23, and the heat dissipation efficiency of the lubricating oil heat dissipation portion 23 is reduced. Meanwhile, the fuel quantity of the fuel with higher temperature flowing out of the electronic equipment radiating part 22 and flowing into the hydraulic oil radiating part 24 can be increased, and the radiating efficiency of the hydraulic oil radiating part 24 is improved.
In step S18, the fifth temperature probe 243 detects that the fuel temperature T5 of the hydraulic oil heat dissipation portion 24 is greater than the first temperature threshold, and controls the opening of the fifth flow regulating valve 242 to increase, so that more fuel flows into the hydraulic oil heat dissipation portion 24, thereby taking away heat transferred during operation of the hydraulic oil device.
It will be understood by those of ordinary skill in the art that the foregoing embodiments are specific examples of implementing the disclosure, and that various changes in form and details may be made therein without departing from the spirit and scope of the disclosure.
Claims (11)
1. An aircraft step heat sink, the aircraft step heat sink comprising:
the device comprises an oil supply device, a first heat dissipation device, a second heat dissipation device, an engine, an auxiliary oil supply device, a hot oil return device and a first one-way valve;
an oil outlet of the oil supply device is communicated with the first end of the first heat dissipation device; an oil outlet of the oil supply device is communicated with a first end of the auxiliary oil supply device; the oil return port of the oil supply device is communicated with the first end of the hot oil return device; the first heat dissipation device comprises an electronic equipment heat dissipation part, a lubricating oil heat dissipation part and a hydraulic oil heat dissipation part; an oil outlet of the oil supply device is communicated with a first end of the electronic equipment radiating part; the second end of the electronic equipment heat dissipation part is communicated with the first end of the lubricating oil heat dissipation part; the second end of the electronic equipment heat dissipation part is communicated with the first end of the hydraulic oil heat dissipation part; the second end of the lubricating oil heat dissipation part is communicated with the second end of the hydraulic oil heat dissipation part and forms the second end of the first heat dissipation device;
the second end of the first heat radiating device is communicated with the second end of the hot oil return device; the second end of the first heat dissipation device is communicated with the first end of the second heat dissipation device through the first one-way valve; the second heat dissipation device is used for performing heat dissipation treatment on the engine shell;
the second end of the auxiliary oil supply device is communicated with the first end of the second heat dissipation device;
the first one-way valve prevents fuel oil in the second heat dissipating device and the auxiliary fuel supply device from flowing into the first heat dissipating device; the second end of the second heat sink is in communication with the engine.
2. An aircraft step heat sink according to claim 1, wherein,
the second heat dissipation device comprises a second temperature probe; the second temperature probe is arranged at the second end of the second heat dissipation device, and the temperature of the fuel oil flowing out of the second end of the second heat dissipation device is obtained; the auxiliary oil supply device comprises a second flow regulating valve; the second temperature probe is electrically connected with the second flow regulating valve.
3. An aircraft step heat sink according to claim 2, wherein,
the first heat dissipation device comprises a first temperature probe; the first temperature probe is arranged at the second end of the first heat dissipation device, and the temperature of fuel oil flowing out of the second end of the first heat dissipation device is obtained; the hot oil return device comprises a first flow regulating valve; the first temperature probe is electrically connected with the first flow regulating valve.
4. An aircraft step heat sink according to claim 3, wherein,
the electronic equipment radiating part comprises an electronic equipment radiator, a third flow regulating valve and a third temperature probe; an oil outlet of the oil supply device is communicated with the first end of the third flow regulating valve; the second end of the third flow regulating valve is communicated with the first end of the radiator of the electronic equipment; the second end of the electronic equipment radiator is set as the second end of the electronic equipment radiating part; the third temperature probe is arranged at the second end of the radiator of the electronic equipment, and the temperature of the fuel oil flowing out of the second end of the radiator of the electronic equipment is obtained.
5. An aircraft step heat sink as recited in claim 4, wherein,
the lubricating oil heat dissipation part comprises a lubricating oil radiator, a fourth flow regulating valve, a second one-way valve and a fourth temperature probe; the fourth flow regulating valve, the second one-way valve and the lubricating oil radiator are sequentially communicated; one end of the fourth flow regulating valve, which is far away from the second one-way valve, is arranged as a first end of the lubricating oil heat dissipation part; one end of the lubricating oil radiator, which is far away from the second one-way valve, is arranged as a second end of the lubricating oil radiating part; the second one-way valve prevents fuel in the lubricating oil radiator from flowing to the fourth flow regulating valve; the fourth temperature probe is arranged at the second end of the lubricating oil heat dissipation part, and the temperature of the fuel oil flowing out of the second end of the lubricating oil heat dissipation part is obtained.
6. An aircraft step heat sink as recited in claim 5, wherein,
the first heat dissipation device further comprises a sixth flow regulating valve; the first end of the sixth flow regulating valve is communicated with an oil outlet of the oil supply device; the second end of the sixth flow regulating valve is communicated with one end, close to the second one-way valve, of the lubricating oil heat dissipation part.
7. An aircraft step heat sink as recited in claim 6, wherein,
the hydraulic oil heat dissipation part comprises a hydraulic oil radiator, a fifth flow regulating valve and a fifth temperature probe; the first end of the fifth flow regulating valve is communicated with the second end of the electronic equipment radiating part; the second end of the fifth flow regulating valve is communicated with the first end of the hydraulic oil radiator; the second end of the hydraulic oil radiator is set as the second end of the hydraulic oil radiating part; the fifth temperature probe is arranged at the second end of the hydraulic oil heat dissipation part, and the temperature of the fuel oil flowing out of the second end of the hydraulic oil heat dissipation part is obtained.
8. A control method for an aircraft step heat sink as claimed in claim 7, characterized in that,
the control method comprises the following steps:
step S11, based on the starting of the aircraft, the fuel oil supplied by the fuel oil supply device sequentially passes through the first heat dissipation device and the second heat dissipation device and enters the engine for combustion;
step S12, controlling the opening of a second flow regulating valve based on the fact that the temperature T2 acquired by the second temperature probe is larger than a second temperature threshold;
step S13, based on the second flow regulating valve being opened and the temperature T1 acquired by the first temperature probe being greater than a first temperature threshold, the first flow regulating valve is opened; wherein the second flow regulating valve opening is larger than the first flow regulating valve opening.
9. The method of claim 8, wherein,
the control method further includes:
and step S14, controlling the second flow regulating valve to be opened and controlling the first flow regulating valve to be closed based on the fact that the temperature T2 acquired by the second temperature probe is smaller than or equal to the second temperature threshold and larger than a third temperature threshold.
10. The method of claim 8, wherein,
the control method further includes:
and step S15, based on the fact that the temperature T2 acquired by the second temperature probe is smaller than or equal to a third temperature threshold, closing a second flow regulating valve, and controlling the first flow regulating valve to be closed.
11. The method of claim 8, wherein,
the control method further includes:
step S16, controlling the opening of the third flow regulating valve to be increased based on the fact that the temperature T3 acquired by the third temperature probe is larger than the first temperature threshold;
step S17, controlling the opening of the sixth flow regulating valve to be increased based on the fact that the temperature T4 acquired by the fourth temperature probe is larger than the first temperature threshold;
and S18, controlling the opening of the fifth flow regulating valve to be increased based on the fact that the temperature T5 acquired by the fifth temperature probe is greater than the first temperature threshold.
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3300965A (en) * | 1964-05-08 | 1967-01-31 | Rolls Royce | Gas turbine engine fuel heating and oil cooling system |
| US4505124A (en) * | 1983-09-22 | 1985-03-19 | The United States Of America As Represented By The Secretary Of The Air Force | Heat management system for aircraft |
| US6182435B1 (en) * | 1997-06-05 | 2001-02-06 | Hamilton Sundstrand Corporation | Thermal and energy management method and apparatus for an aircraft |
| US6415595B1 (en) * | 2000-08-22 | 2002-07-09 | Hamilton Sundstrand Corporation | Integrated thermal management and coolant system for an aircraft |
| CN106917684A (en) * | 2015-12-08 | 2017-07-04 | 通用电气公司 | Heat management system |
| CN108425752A (en) * | 2017-02-15 | 2018-08-21 | 波音公司 | Reversed air cycle machine RACM heat management systems and method |
| CN109803891A (en) * | 2016-10-11 | 2019-05-24 | 西门子股份公司 | For the drive system with internal combustion engine and the vehicles of fuel tank |
| CN109812338A (en) * | 2017-11-21 | 2019-05-28 | 通用电气公司 | Heat management system |
| CN109969411A (en) * | 2018-12-31 | 2019-07-05 | 北京航空航天大学 | A kind of aircraft fuel oil heat management system and method with cold-storage ability |
| CN110920914A (en) * | 2019-12-06 | 2020-03-27 | 南京航空航天大学 | Comprehensive thermal management and regulation system for airplane |
| CN112623233A (en) * | 2020-12-24 | 2021-04-09 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Self-adaptive power and heat management system for airplane |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9561857B2 (en) * | 2013-02-06 | 2017-02-07 | Raytheon Company | Aircraft thermal management system for cooling using expendable coolants |
| EP3730763B1 (en) * | 2019-04-17 | 2023-02-15 | Raytheon Technologies Corporation | Dynamic thermal load monitoring and mitigation for aircraft systems |
-
2023
- 2023-07-04 CN CN202310806344.0A patent/CN116534263B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3300965A (en) * | 1964-05-08 | 1967-01-31 | Rolls Royce | Gas turbine engine fuel heating and oil cooling system |
| US4505124A (en) * | 1983-09-22 | 1985-03-19 | The United States Of America As Represented By The Secretary Of The Air Force | Heat management system for aircraft |
| US6182435B1 (en) * | 1997-06-05 | 2001-02-06 | Hamilton Sundstrand Corporation | Thermal and energy management method and apparatus for an aircraft |
| US6415595B1 (en) * | 2000-08-22 | 2002-07-09 | Hamilton Sundstrand Corporation | Integrated thermal management and coolant system for an aircraft |
| CN106917684A (en) * | 2015-12-08 | 2017-07-04 | 通用电气公司 | Heat management system |
| CN109803891A (en) * | 2016-10-11 | 2019-05-24 | 西门子股份公司 | For the drive system with internal combustion engine and the vehicles of fuel tank |
| CN108425752A (en) * | 2017-02-15 | 2018-08-21 | 波音公司 | Reversed air cycle machine RACM heat management systems and method |
| CN109812338A (en) * | 2017-11-21 | 2019-05-28 | 通用电气公司 | Heat management system |
| CN109969411A (en) * | 2018-12-31 | 2019-07-05 | 北京航空航天大学 | A kind of aircraft fuel oil heat management system and method with cold-storage ability |
| CN110920914A (en) * | 2019-12-06 | 2020-03-27 | 南京航空航天大学 | Comprehensive thermal management and regulation system for airplane |
| CN112623233A (en) * | 2020-12-24 | 2021-04-09 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Self-adaptive power and heat management system for airplane |
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|---|---|
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