CN211527847U - Aviation oil-cooled generator fuel and lubricating oil integrated test system - Google Patents
Aviation oil-cooled generator fuel and lubricating oil integrated test system Download PDFInfo
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- CN211527847U CN211527847U CN201921967658.4U CN201921967658U CN211527847U CN 211527847 U CN211527847 U CN 211527847U CN 201921967658 U CN201921967658 U CN 201921967658U CN 211527847 U CN211527847 U CN 211527847U
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Abstract
The application relates to a fuel-lubricating oil integrated test system of an aviation oil-cooled generator, which comprises a lubricating oil circulation subsystem, wherein a tested generator, a pressure regulating valve, a lubricating oil radiator and an oil-gas separation subsystem are arranged on a circulation pipeline of the system, the pressure regulating valve is used for regulating the flow resistance of the pipeline, and the oil-gas separation subsystem is provided with an oil supplementing vent valve which is used for regulating the content of lubricating oil in the circulation pipeline; the oil injection subsystem is used for supplying lubricating oil to the lubricating oil circulation subsystem; the fuel subsystem comprises a fuel circulation pipeline and a water-cooling heat dissipation circulation pipeline, the fuel circulation pipeline exchanges heat with the water-cooling heat dissipation circulation pipeline through a water-cooling radiator, and the fuel circulation pipeline exchanges heat with the lubricating oil circulation subsystem through a lubricating oil radiator. The method and the device check the heating amount and the cooling effect of the generator under the conditions of pipeline flow resistance, lubricating oil gas content and fuel oil cooling on the equivalent machine, and improve the reliability and the stability of the test.
Description
Technical Field
The application belongs to the technical field of oil-cooled generator tests, and particularly relates to an aviation oil-cooled generator fuel and lubricating oil integrated test system.
Background
At present, when heating value and cooling verification are carried out on domestic and military aviation oil-cooled generators, the motors are cooled in a mode of cooling generator lubricating oil by using circulating water, the cooling condition is greatly different from the actual cooling condition on the machine, and the generator lubricating oil is cooled by using fuel oil on the machine, so that the heating value and cooling verification check on the motors cannot be equivalent to the on-machine check on the basis of different specific heat and viscosity of water and the fuel oil; secondly, the flow resistance and the gas content of the lubricating oil of different external pipelines have great influence on the heat loss and the efficiency of the generator, so that the reliability of the test result is low.
SUMMERY OF THE UTILITY MODEL
In order to simulate actual cooling environment, coolant and the outer pipeline flow resistance of equivalent generator on the aircraft, examine the generator and on-machine pipeline flow resistance, calorific capacity and cooling effect under the different proportion air content, the fuel cooling condition, verify the reliability and the stability of generator operation, this application provides an aviation oil-cooled generator fires oil and slide integration test system, includes:
the lubricating oil circulation subsystem comprises a tested generator, a pressure regulating valve, a lubricating oil radiator and an oil-gas separation subsystem on a circulation pipeline, wherein the pressure regulating valve is used for regulating the flow resistance of the pipeline, and the oil-gas separation subsystem is provided with an oil supplementing vent valve which is used for regulating the content of lubricating oil in the circulation pipeline;
the oil injection subsystem is used for supplying lubricating oil to the lubricating oil circulation subsystem;
the fuel subsystem comprises a fuel circulation pipeline and a water-cooling heat dissipation circulation pipeline, the fuel circulation pipeline exchanges heat with the water-cooling heat dissipation circulation pipeline through a water-cooling radiator, and the fuel circulation pipeline exchanges heat with the lubricating oil circulation subsystem through a lubricating oil radiator.
Preferably, a flow sensor is arranged on a circulating pipeline of the lubricating oil circulating subsystem, and two ends of the flow sensor are connected with a pressure reducing valve in parallel.
Preferably, the lubricating oil inlet and the lubricating oil outlet of the generator to be tested are both provided with a pressure sensor and a temperature sensor.
Preferably, the oil-gas separation subsystem comprises a first electromagnetic valve F1 arranged on a circulation pipeline of the lubricating oil circulation subsystem, two ends of the first electromagnetic valve F1 are respectively connected with a lubricating oil sampling pipeline in parallel through a second electromagnetic valve F2 and a third electromagnetic valve F3, an oil supplementing vent valve is arranged on the lubricating oil sampling pipeline, and a sampling valve is arranged at the bottom end of the lubricating oil sampling pipeline.
Preferably, the oiling subsystem comprises a main circulation pipeline, the main circulation pipeline comprises a lubricating oil pump and a lubricating oil tank, the lubricating oil pump extracts lubricating oil from the lubricating oil tank and can flow back to the lubricating oil tank through the main circulation pipeline, a three-way switch is arranged on the main circulation pipeline, and the other outlet of the three-way switch supplies the lubricating oil to the lubricating oil circulation subsystem through a one-way valve.
Preferably, the outlet end of the lubricating oil pump is connected to the lubricating oil tank through a first return pipeline, and the first return pipeline is provided with a pressure reducing valve.
Preferably, the fuel subsystem comprises a fuel pump and a fuel tank, the fuel pump pumps fuel, the fuel is firstly radiated by a water-cooled radiator and then divided into two paths, the first path flows back to the fuel tank after passing through a first electric regulating valve and a lubricating oil radiator, and the second path flows back to the fuel tank through a second electric regulating valve.
Preferably, the outlet of the fuel pump is further connected to the fuel tank through a second return line, and a pressure reducing valve is arranged on the second return line.
Preferably, the fuel subsystem is provided with a flow sensor in the first path.
Preferably, the fuel subsystem is provided with a pressure sensor and a temperature sensor at the fuel inlet and outlet ends of the lubricating oil radiator.
The method and the device for testing the oil-cooled generator achieve the testing verification requirements of the oil-cooled generator under the condition of simulating the cooling system in the installed state, examine the flow resistance of the generator on the equivalent machine, the gas content of lubricating oil and the heating value and the cooling effect of the generator under the condition of cooling fuel oil, and improve the reliability and the stability of the test.
Drawings
FIG. 1 is a schematic pipeline connection diagram of a preferred embodiment of the fuel-oil integrated test system of the aviation oil-cooled generator.
FIG. 2 is a schematic diagram of an oil-gas separation subsystem of the aviation oil-cooled generator fuel-lubricating oil integrated test system.
Wherein, 1-lubricating oil circulation subsystem, 2-oiling subsystem, 3-fuel subsystem, 4-measuring and controlling subsystem, and 5-industrial water;
11-a tested generator, 12-a pressure regulating valve, 13-a lubricating oil radiator, 14-an oil-gas separation subsystem, 141-a lubricating oil sampling pipeline, 142-an oil supplementing vent valve, 143-a sampling valve, 15-a flow sensor, 16-a pressure reducing valve and 17-a lubricating oil filter; 21-a lubricating oil pump, 22-a lubricating oil tank, 23-a one-way valve, 24-a three-way switch and 25-a pressure reducing valve; 31-a water-cooled radiator, 32-a fuel pump, 33-a fuel tank, 34-a first electric regulating valve, 35-a second electric regulating valve, 36-a pressure reducing valve and 37-a flow sensor; 38-electric regulating valve, 39-flow sensor.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides an aviation oil-cooled generator fires oil integration test system, mainly include as shown in fig. 1:
the system comprises a lubricating oil circulation subsystem 1, a tested generator 11, a pressure regulating valve 12, a lubricating oil radiator 13 and an oil-gas separation subsystem 14 are arranged on a circulation pipeline of the system, wherein the pressure regulating valve 12 is used for regulating the flow resistance of the pipeline, and the oil-gas separation subsystem 14 is provided with an oil supplementing vent valve which is used for regulating the content of lubricating oil in the circulation pipeline;
the oil injection subsystem 2 is used for supplying lubricating oil to the lubricating oil circulation subsystem 1;
the fuel oil subsystem 3 comprises a fuel oil circulation pipeline and a water-cooling heat dissipation circulation pipeline, the fuel oil circulation pipeline exchanges heat with the water-cooling heat dissipation circulation pipeline through a water-cooling radiator 31, and the fuel oil circulation pipeline exchanges heat with the lubricating oil circulation subsystem 1 through a lubricating oil radiator 13.
In some alternative embodiments, a flow sensor 15 is disposed on the circulation pipeline of the oil circulation subsystem 1, and a pressure reducing valve 16 is connected in parallel to two ends of the flow sensor 15.
In some optional embodiments, the lubricant inlet and the lubricant outlet of the generator 11 under test are provided with a pressure sensor and a temperature sensor.
In this application, at first, carry out the oiling through the lubricating oil subsystem to the tested article, the lubricating oil is in the lubricating oil tank is injected into tested product to the lubricating oil through the lubricating oil pump. During oil injection, the oil injection pressure is monitored through a pressure sensor. When the pressure in the product is larger than a set threshold value, the pressure relief valve and the electromagnetic valve start to work, and the tested product is guaranteed not to be damaged due to overpressure. After the oil injection is finished, the fuel subsystem starts to work, the fuel pump circularly cools the fuel in the fuel tank through the fuel water radiator, and the flow of the fuel can be changed by changing the frequency of the fuel pump. The fuel oil exchanges heat with the tested lubricating oil through the fuel oil-lubricating oil heat exchanger. During the working period of the system, the flow of the lubricating oil during the working of the product is monitored by a flowmeter, and the temperature and the pressure of the lubricating oil at the inlet and the outlet of the tested product are respectively monitored by a pressure sensor and a temperature sensor.
In some optional embodiments, referring to fig. 2, the oil-gas separation subsystem 14 includes a first solenoid valve F1 disposed on the circulation line of the oil circulation subsystem 1, two ends of the first solenoid valve F1 are respectively connected in parallel to an oil sampling line 141 through a second solenoid valve F2 and a third solenoid valve F3, an oil supplementing vent valve 142 is disposed on the oil sampling line 141, and a sampling valve 143 is disposed at the bottom end of the oil sampling line 141.
With reference to fig. 1 and fig. 2, when the generator 11 to be tested starts to operate, the electromagnetic valve F1 in the oil-gas separation subsystem is opened, and the electromagnetic valves F2 and F3 are closed. After the generator reaches the working rotating speed, the oil pump drives the lubricating oil to circulate in the lubricating oil circulation subsystem of the generator, and the lubricating oil exchanges heat with the fuel oil from the fuel oil subsystem through the fuel oil-lubricating oil radiator of the airplane. A pressure reducing valve is connected beside the lubricating oil flow sensor in parallel, and is opened when the lubricating oil flow sensor is blocked, so that a lubricating oil pipeline is ensured to be smooth; during the working process of the generator, the electromagnetic valve F1 in the oil-gas separation subsystem is changed from an open state to a closed state, and the electromagnetic valves F2 and F3 are changed from the closed state to the open state. After a period of time, the solenoid valve F1 is opened, F2 and F3 are closed, the oil sample is sealed in the oil sampling pipeline, and the oil sample is taken at the valve at the lowest point of the sampling pipeline. And after the oil-gas ratio measurement sampling, stopping the generator. The solenoid valves F2, F3 are in a closed state. Opening two oil-supplementing vent valves, pouring the lubricating oil in the measuring cylinder into a lubricating oil sampling pipeline from one valve, and then closing the two oil-supplementing vent valves or adjusting the lubricating oil content of the lubricating oil sampling pipeline to achieve the purpose of changing the gas content proportion; in addition, the flow resistance of the outer pipeline is changed by adjusting the pressure regulating valve, so that the running reliability and stability of the generator under the conditions of different flow resistances of the outer pipeline and different gas contents of lubricating oil are verified.
In some alternative embodiments, the oiling subsystem 2 comprises a main circulation pipeline, the main circulation pipeline comprises a lubricating oil pump 21 and a lubricating oil tank 22, the lubricating oil pump 21 draws lubricating oil from the lubricating oil tank 22 and can flow back to the lubricating oil tank 22 through the main circulation pipeline, a three-way switch 24 is arranged on the main circulation pipeline, and the other outlet of the three-way switch 24 supplies the lubricating oil to the lubricating oil circulation subsystem 1 through a one-way valve 23.
In some alternative embodiments, the outlet end of the lube pump 21 is connected to the lube tank 22 by a first return line, on which a pressure relief valve 25 is provided.
In some alternative embodiments, the fuel subsystem 3 includes a fuel pump 32 and a fuel tank 33, the fuel pump 32 pumps fuel and then first passes through a water-cooled radiator 31 to dissipate heat, and then is divided into two paths, the first path flows back to the fuel tank 33 after passing through a first electric regulating valve 34 and a lubricating oil radiator 13, and the second path flows back to the fuel tank 33 through a second electric regulating valve 35.
Referring to fig. 1, in another circulation loop of the water-cooled radiator 31, water is pumped from the industrial water 5 by a water pump and flows back through a water filter, an electric regulating valve 38, the water-cooled radiator 31 and a flow sensor 39, so that the fuel oil is cooled.
In some alternative embodiments, the outlet of the fuel pump 32 is also connected to the fuel tank 33 by a second return line, on which a pressure relief valve 36 is provided.
In some alternative embodiments, the fuel subsystem 3 is provided with a flow sensor 37 in the first path.
In some alternative embodiments, the fuel subsystem 3 is provided with a pressure sensor and a temperature sensor at the fuel inlet and outlet ends of the lubricant radiator 13.
The application adopts an indirect heat exchange method to accurately control the temperature of the aviation lubricating oil. The temperature of a lubricating oil inlet is taken as a control object, a plunger pump is selected as an oil supply pump of a fuel oil system, cooling water is used for cooling fuel oil through a heat exchanger, the oil temperature of the lubricating oil on the other side of the heat exchanger is controlled by changing the flow of the fuel oil, the equivalence of the actual cooling condition, the flow resistance of a cooling pipeline and the air content of the lubricating oil on an airplane is realized, the development requirements of the heating value of a generator and the cooling effect of the heat exchanger are met, and the whole system can be remotely controlled and monitored through a measurement and control subsystem 4.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides an aviation oil-cooled generator fires oil integration test system which characterized in that includes:
the system comprises a lubricating oil circulation subsystem (1), a tested generator (11), a pressure regulating valve (12), a lubricating oil radiator (13) and an oil-gas separation subsystem (14) are arranged on a circulation pipeline of the system, the pressure regulating valve (12) is used for regulating the flow resistance of the pipeline, and the oil-gas separation subsystem (14) is provided with an oil supplementing vent valve which is used for regulating the content of lubricating oil in the circulation pipeline;
the oil injection subsystem (2) is used for supplying lubricating oil into the lubricating oil circulation subsystem (1);
and the fuel subsystem (3) comprises a fuel circulation pipeline and a water-cooling heat dissipation circulation pipeline, the fuel circulation pipeline exchanges heat with the water-cooling heat dissipation circulation pipeline through a water-cooling radiator (31), and the fuel circulation pipeline exchanges heat with the lubricating oil circulation subsystem (1) through a lubricating oil radiator (13).
2. The integrated fuel-oil testing system of the aviation oil-cooled generator according to claim 1, characterized in that a flow sensor (15) is arranged on a circulation pipeline of the oil circulation subsystem (1), and a pressure reducing valve (16) is connected in parallel with two ends of the flow sensor (15).
3. The integrated fuel-oil testing system for the aviation oil-cooled generator according to claim 1, wherein a pressure sensor and a temperature sensor are arranged at an oil inlet and an oil outlet of the tested generator (11).
4. The integrated fuel-oil testing system of the aviation oil-cooling generator of claim 1, wherein the oil-gas separation subsystem (14) comprises a first solenoid valve F1 disposed on a circulation pipeline of the oil circulation subsystem (1), two ends of the first solenoid valve F1 are respectively connected in parallel with an oil sampling pipeline (141) through a second solenoid valve F2 and a third solenoid valve F3, an oil supplementing vent valve (142) is disposed on the oil sampling pipeline (141), and a sampling valve (143) is disposed at the bottom end of the oil sampling pipeline (141).
5. The aviation oil-cooled generator fuel-oil integrated test system according to claim 1, wherein the oil injection subsystem (2) comprises a main circulation pipeline, the main circulation pipeline comprises a lubricating oil pump (21) and a lubricating oil tank (22), the lubricating oil pump (21) pumps lubricating oil from the lubricating oil tank (22) and can flow back to the lubricating oil tank (22) through the main circulation pipeline, a three-way switch (24) is arranged on the main circulation pipeline, and the other outlet of the three-way switch (24) supplies lubricating oil to the lubricating oil circulation subsystem (1) through a one-way valve (23).
6. The integrated fuel-oil testing system for the aircraft oil-cooled generator according to claim 5, wherein the outlet end of the fuel oil pump (21) is connected to the fuel tank (22) through a first return line, and a pressure reducing valve (25) is arranged on the first return line.
7. The integrated fuel-oil testing system of the aviation oil-cooled generator as claimed in claim 1, wherein the fuel subsystem (3) comprises a fuel pump (32) and a fuel tank (33), the fuel pump (32) pumps fuel oil and then firstly radiates the heat through a water-cooled radiator (31), and then the fuel oil is divided into two paths, the first path flows back to the fuel tank (33) after passing through a first electric regulating valve (34) and a lubricating oil radiator (13), and the second path flows back to the fuel tank (33) through a second electric regulating valve (35).
8. The integrated aviation oil-cooled generator and lubricating oil testing system as claimed in claim 7, characterized in that the outlet of the fuel pump (32) is also connected to a fuel tank (33) through a second return line, and a pressure reducing valve (36) is arranged on the second return line.
9. The integrated aviation oil-cooled generator and fuel oil testing system according to claim 7, characterized in that the fuel subsystem (3) is provided with a flow sensor (37) on the first path.
10. The integrated fuel-oil testing system for the aviation oil-cooled generator as claimed in claim 7, wherein the fuel subsystem (3) is provided with a pressure sensor and a temperature sensor at the fuel inlet and outlet ends of the lubricating oil radiator (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921967658.4U CN211527847U (en) | 2019-11-14 | 2019-11-14 | Aviation oil-cooled generator fuel and lubricating oil integrated test system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921967658.4U CN211527847U (en) | 2019-11-14 | 2019-11-14 | Aviation oil-cooled generator fuel and lubricating oil integrated test system |
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| CN211527847U true CN211527847U (en) | 2020-09-18 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113218447A (en) * | 2021-04-29 | 2021-08-06 | 中汽研汽车检验中心（天津）有限公司 | Oil level self-balancing test equipment for oil-cooled motor test |
| CN115126636A (en) * | 2022-07-12 | 2022-09-30 | 武汉东测科技有限责任公司 | Fuel oil system test bench |
-
2019
- 2019-11-14 CN CN201921967658.4U patent/CN211527847U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113218447A (en) * | 2021-04-29 | 2021-08-06 | 中汽研汽车检验中心（天津）有限公司 | Oil level self-balancing test equipment for oil-cooled motor test |
| CN113218447B (en) * | 2021-04-29 | 2023-01-10 | 中汽研汽车检验中心（天津）有限公司 | Oil level self-balancing test equipment for oil-cooled motor test |
| CN115126636A (en) * | 2022-07-12 | 2022-09-30 | 武汉东测科技有限责任公司 | Fuel oil system test bench |
| CN115126636B (en) * | 2022-07-12 | 2024-01-09 | 武汉东测科技有限责任公司 | Fuel system test bed |
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