CN116045186A - Civil aviation lubricating oil temperature control system - Google Patents
Civil aviation lubricating oil temperature control system Download PDFInfo
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- CN116045186A CN116045186A CN202310067702.0A CN202310067702A CN116045186A CN 116045186 A CN116045186 A CN 116045186A CN 202310067702 A CN202310067702 A CN 202310067702A CN 116045186 A CN116045186 A CN 116045186A
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- 239000010687 lubricating oil Substances 0.000 title claims abstract description 119
- 239000003921 oil Substances 0.000 claims abstract description 355
- 238000010438 heat treatment Methods 0.000 claims abstract description 89
- 239000000498 cooling water Substances 0.000 claims description 39
- 238000005461 lubrication Methods 0.000 claims description 10
- 239000007788 liquid Substances 0.000 claims description 7
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 102220577960 RPA-interacting protein_H21A_mutation Human genes 0.000 description 23
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 12
- 239000010724 circulating oil Substances 0.000 description 8
- 230000001276 controlling effect Effects 0.000 description 5
- 238000001816 cooling Methods 0.000 description 4
- 238000010992 reflux Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000001105 regulatory effect Effects 0.000 description 3
- 102220479923 Leucine-rich repeat-containing protein 26_H11A_mutation Human genes 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N19/00—Lubricant containers for use in lubricators or lubrication systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N39/00—Arrangements for conditioning of lubricants in the lubricating system
- F16N39/02—Arrangements for conditioning of lubricants in the lubricating system by cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N39/00—Arrangements for conditioning of lubricants in the lubricating system
- F16N39/04—Arrangements for conditioning of lubricants in the lubricating system by heating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N39/00—Arrangements for conditioning of lubricants in the lubricating system
- F16N39/06—Arrangements for conditioning of lubricants in the lubricating system by filtration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N7/00—Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated
- F16N7/38—Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with a separate pump; Central lubrication systems
- F16N7/40—Arrangements for supplying oil or unspecified lubricant from a stationary reservoir or the equivalent in or on the machine or member to be lubricated with a separate pump; Central lubrication systems in a closed circulation system
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N2210/00—Applications
- F16N2210/08—Aircraft
-
- 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)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The invention discloses a civil aviation lubricating oil temperature control system which comprises an oil circuit system, wherein the oil circuit system comprises an oil tank, an oil tank output oil circuit, an oil tank backflow oil circuit, a heating circulation oil circuit, an outward output oil circuit and an outward backflow oil circuit, the heating circulation oil circuit is provided with an oil supply pump and a diverter valve, the output end of the oil tank is connected with the input end of the heating circulation oil circuit through the oil tank output oil circuit, the input end of the heating circulation oil circuit is connected with the input end of an oil supply pump, the output end of the heating circulation oil circuit is connected with an oil supply port through the outward output oil circuit, the backflow input end of the heating circulation oil circuit is connected with an oil return port through the outward backflow oil circuit, and the first output end of the diverter valve is connected with the input end of the oil tank through the oil tank backflow oil circuit; the lubricating oil circulated in the heating circulation oil path will continuously generate friction with the heating circulation oil path to raise the temperature, and the lubricating oil in the oil tank is output and mixed to lower the temperature. The invention has short heating time for lubricating oil, uniform heating, simple structure, environmental protection and energy saving.
Description
Technical Field
The invention relates to a civil aviation lubricating oil temperature control system.
Background
Aviation lubricating oil refers to lubricating oil which is used for lubricating and cooling systems such as engines or APUs in civil aircrafts. At present, the latest standard to be followed by civil aviation lubricating oil is MIL-L-23699, the common brand name is MOBILJET II, and the temperature control system is used for controlling the temperature of the lubricating oil.
The lubricating oil temperature control system is a system for heating and regulating the temperature of lubricating oil in a system or a pipeline to meet specific requirements, and is usually composed of a lubricating oil source, a heater, a heat exchanger, a cooling water tower, a temperature detector, a closed-loop or open-loop control circuit, a regulating valve and the like, and is commonly used for controlling the temperature of the lubricating oil of a civil aviation lubricating oil part test board.
The traditional lubricating oil temperature control system generally adopts a submerged electric wire heating mode and a cooling water tower cooling mode to realize the control of the lubricating oil temperature, and the invention adopts a brand new pipeline self-heating type civil aviation lubricating oil temperature control system.
Disclosure of Invention
The invention aims to solve the technical problem of providing a civil aviation lubricating oil temperature control system which has the advantages of short heating time, uniform heating, simple structure, environmental protection and energy conservation.
The technical scheme adopted by the invention is as follows:
a civil aviation lubricating oil temperature control system is characterized in that: the oil circuit system comprises an oil tank, an oil tank output oil circuit, an oil tank return oil circuit, a heating circulation oil circuit, an outward output oil circuit and an outward return oil circuit, wherein an oil supply pump and a flow dividing valve are arranged on the heating circulation oil circuit, the output end of the oil tank is connected with the input end of the heating circulation oil circuit through the oil tank output oil circuit, the input end of the heating circulation oil circuit is connected with the input end of an oil supply pump, the output end of the heating circulation oil circuit is connected with an oil supply port through the outward output oil circuit, the return input end of the heating circulation oil circuit is connected with an oil return port through the outward return oil circuit, and the first output end of the flow dividing valve is connected with the input end of the oil tank through the oil tank return oil circuit; the oil supply port and the oil return port are used for being connected with external parts;
part of the lubricating oil output from the oil tank circulates in the heating circulation oil path, the circulated lubricating oil continuously generates friction with the heating circulation oil path, thereby raising the temperature of the lubricating oil in circulation, and the temperature of the lubricating oil in the heating circulation oil path is lowered by outputting and mixing the lubricating oil in the oil tank into the lubricating oil in the heating circulation oil path; the lubricating oil in the heating circulation oil way can be output to external parts through the outward output oil way, and the lubricating oil in the heating circulation oil way can flow back to the oil tank through the oil tank return oil way.
Optionally, the oil tank return oil way is provided with a water-oil heat exchanger, the civil aviation lubricating oil temperature control system is provided with a cooling water circulation pipeline, the cooling water circulation pipeline is connected with the water-oil heat exchanger, and when cooling water circulates through the cooling water circulation pipeline, the cooling water takes away the temperature of lubricating oil flowing through the water-oil heat exchanger.
Optionally, a safety valve is arranged on the heating circulation oil path, a pressure relief end of the safety valve is connected with a pressure relief oil path, and lubricating oil circulating in the heating circulation oil path is rubbed with the safety valve to increase temperature.
Optionally, an oil way stop valve is arranged on the oil tank output oil way.
Optionally, the oil tank output oil way is provided with a first oil filter, the heating circulation oil way is provided with a second oil filter, and the oil tank return oil way is provided with a third oil filter.
Optionally, the input end of the diverter valve is connected with the oil tank return oil way through a first valve.
Optionally, a flowmeter is arranged on the outward output oil path.
Optionally, the civil aviation lubricating oil temperature control system comprises an electric control system, the electric control system is provided with a first temperature sensor, a second temperature sensor and a third temperature sensor, the first temperature sensor detects the temperature of lubricating oil in the oil tank, the second temperature sensor detects the temperature of lubricating oil in the heating circulation oil path, the third temperature sensor detects the temperature of lubricating oil in the outward output oil path, and a control end of the flow dividing valve and a control end of the oil supply pump are respectively electrically connected with the electric control system.
Optionally, the electric control system comprises a first temperature controller, a second temperature controller and an industrial personal computer, wherein the first temperature sensor is electrically connected with a temperature signal acquisition end of the first temperature controller, the second temperature sensor is electrically connected with a temperature signal acquisition end of the second temperature controller, and the third temperature sensor is electrically connected with a temperature signal acquisition end of the industrial personal computer.
Optionally, a temperature switch and a liquid level switch are arranged in the oil tank, and the temperature switch and the liquid level switch are respectively and electrically connected with the electric control system.
Compared with the prior art, the invention has the following beneficial effects:
(1) The invention has low energy consumption.
According to the invention, part of lubricating oil in the oil tank is heated through the heating circulating oil way, and the lubricating oil in the whole oil tank is not required to be heated like a traditional lubricating oil temperature control system, so that the consumed energy is reduced greatly.
(2) The temperature of the lubricating oil of the invention is raised and lowered rapidly.
According to the invention, part of the lubricating oil in the oil tank is heated through the heating circulating oil way, the heated lubricating oil is small in quantity, and the lubricating oil in the whole oil tank is not required to be heated like a traditional lubricating oil temperature control system, so that the temperature of the lubricating oil is raised more quickly, and the lubricating oil after reaching the temperature can be output to external parts through the outward output oil way. The invention can realize the reduction of the temperature of the lubricating oil in the oil tank by outputting the lubricating oil in the oil tank and mixing the lubricating oil into the lubricating oil in the heating circulation oil path, and can lead the cooling speed to be faster.
(3) The lubricating oil is heated uniformly.
The temperature of the lubricating oil is increased by continuously rubbing the lubricating oil circulated in the heating circulating oil way with the heating circulating oil way, the internal friction of lubricating oil molecules is basically used for heating, the heating is uniform, and the lubricating oil is not easy to age. In the traditional mode of heating by the wire heater, the temperature of the lubricating oil closer to the wire heater is higher than that of the lubricating oil farther from the wire heater, the temperature difference exists, and the lubricating oil is more easy to age.
(4) The whole oil way can be sealed, volatilization of lubricating oil can be reduced, damage to personnel and environment is reduced, and the oil way is more environment-friendly. The whole oil way system does not need to be provided with an electric wire, the temperature of the oil tank is maintained at room temperature, and the oil tank can be sealed without considering the pressure relief problem of the oil tank in a high-temperature state.
(5) The invention does not need complex matched equipment and has lower cost. The whole system integrates flow control, temperature control and pressure control into a single closed loop, and realizes all parameter control through the flow dividing valve, so that the structure is simple.
Drawings
FIG. 1 is an oil circuit schematic diagram of an oil circuit system of the present invention;
FIG. 2 is a schematic circuit diagram of a temperature controller portion of the electronic control system of the present invention;
fig. 3 is a schematic circuit diagram of a power supply portion in the electronic control system of the present invention.
The meaning of the reference numerals in the figures:
1-an oil tank output oil way; 2-heating a circulating oil way; 21-an input end of a heating circulating oil circuit; 22-the output end of the heating circulating oil way; 23-a reflux input end of the heating circulating oil way; 3-outputting an oil way outwards; 4-an external reflux oil way; 5-an oil tank return oil path; 6-pressure relief oil way; 7-a cooling water input pipeline; 8-a cooling water output pipeline; 9-discharging oil paths; 10-an oil discharge pipeline; H21A-oil tank; H503A-an oil way stop valve; H504A-first oil filter; H505A-feed pump; H506A-second oil filter; H508A-relief valve; H511A-diverter valve; H512A-water-oil heat exchanger; H514A-first water pressure gauge; H514B-a second water pressure gauge; H515A-waterway filter; H515B-third oil filter; H517A-inlet valve; H519A-oil drain valve; H520A-switch assembly; H2A-an oil drain port; H3A-an oil supply port; H3B-an oil return port; H3D-cooling water input port; an H3E-cooling water output port; H4A-pressure regulator; H5E-a second valve; H7A-a first valve; H8A-a first valve; H9A-third valve; H11A-oil pressure; EH 501A-temperature switch; EH 502A-level switch; EH 503A-first temperature sensor; EH 503B-a second temperature sensor; EH 503C-third temperature sensor; EH 504A-an oil feed pump motor; EH 505A-flow meter; EH 509A-oil pressure switch; EH 513A-solenoid; EH 514A-water pressure switch; E6A-a second temperature controller; E6B-a first temperature controller; E500A-circuit breaker; an E512A-transformer; E514A-contactor.
Detailed Description
The invention is further described below with reference to examples.
In the description of the present invention, it should be understood that references to orientation descriptions such as upper, lower, front, rear, left, right, etc. are based on the orientation or positional relationship shown in the drawings, are merely for convenience of description of the present invention and to simplify the description, and do not indicate or imply that the apparatus or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
In the description of the present invention, a number means one or more, a number means two or more, and greater than, less than, exceeding, etc. are understood to not include the present number, and above, below, within, etc. are understood to include the present number. The description of the first and second is for the purpose of distinguishing between technical features only and should not be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless explicitly defined otherwise, terms such as arrangement, installation, connection, etc. should be construed broadly and the specific meaning of the terms in the present invention can be reasonably determined by a person skilled in the art in combination with the specific contents of the technical scheme.
Examples:
the civil aviation lubricating oil temperature control system of the embodiment is shown in fig. 1, and comprises an oil circuit system and an electric control system.
The oil way system comprises an oil tank H21A, an oil tank output oil way 1, an oil tank return oil way 5, a heating circulation oil way 2, an outward output oil way 3 and an external return oil way 4.
The oil tank output oil path 1 of this embodiment is sequentially provided with an oil path stop valve H503A and a first oil filter H504A from the input end to the output end, the output end of the oil tank H21A is connected with the input end 21 of the heating circulation oil path 2 through the oil tank output oil path 1, and the lubricating oil in the oil tank H21A is output to the heating circulation oil path 2 through the oil tank output oil path 1. The oil passage shutoff valve H503A is used to isolate the oil tank H21A from the oil feed pump H505A during maintenance. An oil pressure switch EH509A is also provided in the tank output oil passage 1 for monitoring the oil pressure in the pipe.
The heating circulation oil path 2 of the present embodiment is provided with an oil feed pump H505A, a second oil filter H506A, a relief valve H508A, a shunt valve H511A and an oil path pressure gauge H11A, the input end 21 of the heating circulation oil path 2 is connected with the input end of the oil feed pump H505A thereof, the output end of the oil feed pump H505A is connected with the output end 22 of the heating circulation oil path 2 through the second oil filter H506A, the output end 22 of the heating circulation oil path 2 is connected with the input end of the relief valve H508A, the output end of the relief valve H508A is connected with the reflux input end 23 of the heating circulation oil path 2, the reflux input end 23 of the heating circulation oil path 2 is connected with the input end 21 of the shunt valve H511A, and the oil path pressure gauge H11A is provided between the output end 22 of the heating circulation oil path 2 and the input end of the relief valve H508A for pressure detection. The pressure relief end of the safety valve H508A is connected with a pressure relief oil way 6, and a pressure regulator H4A is arranged on the pressure relief oil way 6. During the use, part of the lubricating oil output from the oil tank H21A circulates in the heating circulation oil way 2, the circulating lubricating oil continuously generates friction with the heating circulation oil way 2, and mechanical energy is converted into heat energy, so that the temperature of the circulating lubricating oil is increased, and self-heating of the pipeline is realized. By outputting and mixing the lubricating oil in the oil tank H21A into the lubricating oil in the heating circulation oil passage 2, the temperature of the lubricating oil therein is reduced, and by the above-described structure, the control of the temperature increase and the temperature decrease of the lubricating oil can be achieved. The lubricating oil in the heating circulation oil passage 2 may be outputted from the output end 22 to the external component via the outward output oil passage 3, or may be returned to the oil tank H21A via the tank return oil passage 5 from the first output end of the split valve H511A. Wherein the flow of the lubricating oil is powered by the oil feed pump H505A, and the amount of the circulating lubricating oil and the amount of the lubricating oil returned to the oil tank H21A are regulated by the split valve H511A. The second oil filter H506A comprises a TEE-type filter for removing impurities greater than 3 microns from the system, the filter being provided with a visual indicator set to 40 psia.
The first valve H7A and the flow meter EH505A are sequentially disposed on the outward output oil path 3 from the input end to the output end in this embodiment, the output end 22 of the heating circulation oil path 2 is connected with the oil supply port H3A through the outward output oil path 3, the discharge oil path 9 is disposed at the oil supply port H3A, and the second valve H5E is disposed on the discharge oil path 9. The lubricating oil in the heating circulation oil passage 2 can be output to external parts through the outward output oil passage 3.
The outer return oil path 4 of the embodiment is provided with a third valve H9A, and the return input end 23 of the heating circulation oil path 2 is connected with the oil return port H3B through the outer return oil path 4. The oil supply port H3A and the oil return port H3B are used for being connected with an external part, and the lubricating oil heated to the set temperature through the heating circulation oil path 2 can enter the external part through the oil supply port H3A, and the lubricating oil flowing through the external part flows back to the oil path system through the oil return port H3B.
The oil tank return line 5 of the present embodiment is provided with a water-oil heat exchanger H512A and a third oil filter H515B in order from the input end to the output end, and the first output end of the diverter valve H511A is connected to the input end of the oil tank H21A through the oil tank return line 5. By controlling the shunt valve H511A, the lubrication oil in the heating circulation oil passage 2 can be controlled to flow back to the oil tank H21A.
The civil aviation lubricating oil temperature control system of the embodiment is further provided with a cooling water circulation pipeline, the cooling water circulation pipeline is connected with the water-oil heat exchanger H512A, and when cooling water circulates through the cooling water circulation pipeline, the cooling water takes away the temperature of lubricating oil flowing through the water-oil heat exchanger H512A, so that the lubricating oil is cooled. The concrete structure of the cooling water circulation pipeline is as follows: the cooling water circulation pipeline comprises a cooling water input pipeline 7 and a cooling water output pipeline 8, the cooling water input pipeline 7 is connected with the cooling water inlet of the cooling water input port H3D and the cooling water inlet of the water-oil heat exchanger H512A, and the cooling water output pipeline 8 is connected with the cooling water outlet of the cooling water output port H3E and the cooling water outlet of the water-oil heat exchanger H512A. The cooling water input pipeline 7 is sequentially provided with a water inlet valve H517A, a waterway filter H515A, a water pressure switch EH514A, a first water pressure meter H514A and a solenoid valve EH513A from the input end to the output end, the water pressure switch EH514A is used for monitoring water pressure, a system of the cooling water circulation pipeline is closed through the water pressure switch when the water pressure is lower than a set value, and the cooling water output pipeline 8 is provided with a second water pressure meter H514B.
The electric control system is provided with a first temperature controller E6B, a second temperature controller E6A, an industrial personal computer PLC, a first temperature sensor EH503A, a second temperature sensor EH503B and a third temperature sensor EH503C. The first temperature sensor EH503A is provided on the oil tank H21A for detecting the temperature of the lubricating oil in the oil tank H21A; a second temperature sensor EH503B is provided on the heating circulation oil passage 2 for detecting the temperature of the lubricating oil in the heating circulation oil passage 2; a third temperature sensor EH503C is provided on the outward output oil passage 3 for detecting the temperature of the lubricating oil in the outward output oil passage 3. As shown in fig. 2, the first temperature sensor EH503A is electrically connected to the temperature signal collecting end of the first temperature controller E6B, and provides an analog input for the first temperature controller E6B, the second temperature sensor EH503B is electrically connected to the temperature signal collecting end of the second temperature controller E6A, and provides an analog input for the second temperature controller E6A to control the oil cooling temperature, and the third temperature sensor EH503C is electrically connected to the temperature signal collecting end of the industrial personal computer PLC. The control end of the shunt valve H511A and the control end of the oil feed pump H505A are electrically connected to the electronic control system, respectively. The oil feed pump H505A of the present embodiment is provided with an oil feed pump motor EH504A, the oil feed pump motor EH504A is connected to the pump body through the adapter assembly H520A, and the electronic control system controls the oil feed pump by controlling the oil feed pump motor EH 504A. The first temperature sensor EH503A, the second temperature sensor EH503B, and the third temperature sensor EH503C of the present embodiment are all resistive temperature sensors.
In this embodiment, a temperature switch EH501A and a liquid level switch EH502A are disposed in the oil tank H21A, where the temperature switch EH501A and the liquid level switch EH502A are electrically connected to the electric control system respectively, and when the set temperature and the set liquid level are reached, a switch signal is output to the electric control system. The oil tank H21A is further provided with an oil discharge pipe 10, and the oil discharge pipe 10 is provided with an oil discharge valve H519A, and the lubricating oil discharged from the oil discharge pipe 10 is discharged from an oil discharge port H2A for discharging the lubricating oil in the oil tank H21A.
The input end of the diverter valve H511A of the present embodiment is connected to the tank return oil passage 5 through a first valve H8A.
As shown in fig. 3, in terms of power supply, the oil feed pump motor EH504A is connected to a three-phase power supply, and a 60 ampere breaker E500A is provided on the circuit for protection, and is controlled by a contactor E514A. The circuit is also provided with a transformer E512A connected with a three-phase power supply, the transformer E512A reduces 380V voltage to 120V voltage, and the 120V voltage supplies power for another power supply.
One specific working principle of the civil aviation lubricating oil temperature control system of the embodiment is as follows:
at ambient conditions, the tank H21A has a capacity of 75 gallons filled with MIL-L-23699 oil and the temperature switch EH501A in the tank H21A is set to 150F. The level switch EH502A is set to 1/2 level to prevent damage to the system if the oil level is below the allowable limit. The oil feed pump motor EH504A supplies 30gpm of oil at 725psig, and pumps the oil in the oil tank H21A through the oil tank output oil passage 1 via the oil feed pump H505A to the heating circulation oil passage 2. When the second temperature sensor EH503B detects that the temperature T2 of the lubricating oil in the heating circulation oil path 2 is lower than the system set value, a signal is fed back to the industrial personal computer PLC, the industrial personal computer PLC controls the diverter valve H511A, the diverter valve H511A closes the first output end thereof, so that the connection with the oil tank return oil path 5 is closed, the lubricating oil will circulate in the heating circulation oil path 2 under the action of the oil supply pump H505A, and continuously rub against the pipeline and the safety valve H508A, so that the temperature T2 of the lubricating oil in the heating circulation oil path 2 rises. When the temperature T2 of the lubricating oil in the heating circulation oil passage 2 reaches a set value, the system operator connects the external part to the oil supply port H3A and the oil return port H3B, and conveys the lubricating oil of a specific temperature into the external part for use. When the temperature T2 of the lubricating oil in the heating circulation oil path 2 is higher than the required temperature, the industrial personal computer PLC controls the diverter valve H511A, the diverter valve H511A opens the first output end thereof, part of the lubricating oil flows through the first output end, flows through the oil tank return oil path 5 and flows back to the oil tank H21A, and the oil tank H21A is replenished with an equal amount of low-temperature lubricating oil, which is output to the heating circulation oil path 2 through the oil tank output oil path 1 and mixed with the high-temperature lubricating oil in the heating circulation oil path 2, so that the lubricating oil temperature is reduced. The civil aviation lubricating oil temperature control system collects the temperature T1 of lubricating oil in an oil tank H21A through a first temperature sensor EH503A, collects the temperature T2 of the lubricating oil in a heating circulation oil path 2 through a second temperature sensor EH503B, collects the temperature T3 of the lubricating oil in an outward output oil path 3 through a third temperature sensor EH503C, and collects the output flow F of the whole system through a flow meter EH 505A. All the parameters are input to the industrial personal computer PLC, and flow distribution among the loops is affected by controlling the opening and closing angles of the shunt valve H511A, so that closed-loop control of temperature is realized. When the system is operated for too long, and the temperature T1 of the lubricating oil in the oil tank H21A rises to exceed the limit value, the system opens a cooling water circulation pipeline, an external cooling water source (such as municipal water supply or industrial cooling water) is led into a water-oil heat exchanger arranged in the oil tank, the temperature of the lubricating oil in the oil tank H21A is reduced, and when the temperature is reduced to be below the limit value, the system closes the cooling water circulation pipeline.
The civil aviation lubricating oil temperature control system can be applied to a lubricating oil heat exchanger test bed, and at the moment, an external part is a test piece UUT.
The above-mentioned embodiments of the present invention are not intended to limit the scope of the present invention, and the embodiments of the present invention are not limited thereto, and all kinds of modifications, substitutions or alterations made to the above-mentioned structures of the present invention according to the above-mentioned general knowledge and conventional means of the art without departing from the basic technical ideas of the present invention shall fall within the scope of the present invention.
Claims (10)
1. A civil aviation lubricating oil temperature control system is characterized in that: the oil circuit system comprises an oil tank, an oil tank output oil circuit, an oil tank return oil circuit, a heating circulation oil circuit, an outward output oil circuit and an outward return oil circuit, wherein the heating circulation oil circuit is provided with an oil supply pump and a flow dividing valve, the output end of the oil tank is connected with the input end of the heating circulation oil circuit through the oil tank output oil circuit, the input end of the heating circulation oil circuit is connected with the input end of the oil supply pump, the output end of the heating circulation oil circuit is connected with an oil supply port through the outward output oil circuit, the return input end of the heating circulation oil circuit is connected with an oil return port through the outward return oil circuit, and the first output end of the flow dividing valve is connected with the input end of the oil tank through the oil tank return oil circuit; the oil supply port and the oil return port are used for being connected with external parts;
part of the lubricating oil output from the oil tank will circulate in the heating circulation oil path, the circulated lubricating oil will continuously generate friction with the heating circulation oil path, thereby raising the temperature of the lubricating oil in circulation, and the temperature of the lubricating oil in the heating circulation oil path will be lowered by outputting and mixing the lubricating oil in the oil tank into the lubricating oil therein; lubricating oil in the heating circulation oil path can be output to external parts through the outward output oil path, and the lubricating oil in the heating circulation oil path can flow back to the oil tank through the oil tank return oil path.
2. The civil aviation lubrication oil temperature control system of claim 1, wherein: the civil aviation lubricating oil temperature control system is characterized in that a water-oil heat exchanger is arranged on the oil tank return oil way, a cooling water circulation pipeline is arranged on the civil aviation lubricating oil temperature control system and is connected with the water-oil heat exchanger, and when cooling water circulates through the cooling water circulation pipeline, the cooling water takes away the temperature of lubricating oil flowing through the water-oil heat exchanger.
3. The civil aviation lubrication oil temperature control system of claim 1, wherein: the heating circulation oil way is provided with a safety valve, the pressure relief end of the safety valve is connected with a pressure relief oil way, and lubricating oil circulating in the heating circulation oil way is rubbed with the safety valve to improve the temperature.
4. The civil aviation lubrication oil temperature control system of claim 1, wherein: and an oil way stop valve is arranged on the oil tank output oil way.
5. The civil aviation lubrication oil temperature control system of claim 1, wherein: the oil tank output oil way is provided with a first oil filter, the heating circulation oil way is provided with a second oil filter, and the oil tank return oil way is provided with a third oil filter.
6. The civil aviation lubrication oil temperature control system of claim 1, wherein: the input end of the diverter valve is connected with the oil tank return oil way through a first valve.
7. The civil aviation lubrication oil temperature control system of claim 1, wherein: and a flowmeter is arranged on the outward output oil path.
8. The civil aviation lubrication oil temperature control system of claim 1, wherein: the civil aviation lubricating oil temperature control system comprises an electric control system, wherein the electric control system is provided with a first temperature sensor, a second temperature sensor and a third temperature sensor, the first temperature sensor detects the temperature of lubricating oil in an oil tank, the second temperature sensor detects the temperature of the lubricating oil in a heating circulation oil way, the third temperature sensor detects the temperature of the lubricating oil in an outward output oil way, and a control end of a flow dividing valve and a control end of an oil supply pump are respectively and electrically connected with the electric control system.
9. The civil aviation lubrication oil temperature control system of claim 8, wherein: the electric control system comprises a first temperature controller, a second temperature controller and an industrial personal computer, wherein the first temperature sensor is electrically connected with a temperature signal acquisition end of the first temperature controller, the second temperature sensor is electrically connected with a temperature signal acquisition end of the second temperature controller, and the third temperature sensor is electrically connected with a temperature signal acquisition end of the industrial personal computer.
10. The civil aviation lubrication oil temperature control system of claim 8, wherein: the oil tank is internally provided with a temperature switch and a liquid level switch, and the temperature switch and the liquid level switch are respectively and electrically connected with the electric control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310067702.0A CN116045186A (en) | 2023-01-13 | 2023-01-13 | Civil aviation lubricating oil temperature control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310067702.0A CN116045186A (en) | 2023-01-13 | 2023-01-13 | Civil aviation lubricating oil temperature control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116045186A true CN116045186A (en) | 2023-05-02 |
Family
ID=86113148
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310067702.0A Pending CN116045186A (en) | 2023-01-13 | 2023-01-13 | Civil aviation lubricating oil temperature control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116045186A (en) |
-
2023
- 2023-01-13 CN CN202310067702.0A patent/CN116045186A/en active Pending
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