CN112254971A - Test system and method for simulating performance of ventilating bearing cavity of oil pump of aircraft engine - Google Patents
Test system and method for simulating performance of ventilating bearing cavity of oil pump of aircraft engine Download PDFInfo
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- CN112254971A CN112254971A CN202011192233.8A CN202011192233A CN112254971A CN 112254971 A CN112254971 A CN 112254971A CN 202011192233 A CN202011192233 A CN 202011192233A CN 112254971 A CN112254971 A CN 112254971A
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- 238000012360 testing method Methods 0.000 title claims abstract description 33
- 238000000034 method Methods 0.000 title description 4
- 239000003921 oil Substances 0.000 claims abstract description 109
- 238000002156 mixing Methods 0.000 claims abstract description 57
- 239000010687 lubricating oil Substances 0.000 claims abstract description 36
- 238000010438 heat treatment Methods 0.000 claims abstract description 30
- 238000000926 separation method Methods 0.000 claims abstract description 17
- 238000009423 ventilation Methods 0.000 claims abstract description 17
- 238000010792 warming Methods 0.000 claims description 19
- 239000010705 motor oil Substances 0.000 claims description 7
- 238000007789 sealing Methods 0.000 claims description 5
- 238000001914 filtration Methods 0.000 claims description 3
- 238000005086 pumping Methods 0.000 claims description 3
- 239000000446 fuel Substances 0.000 abstract description 8
- 238000005259 measurement Methods 0.000 abstract description 5
- 238000011056 performance test Methods 0.000 abstract description 4
- 238000004088 simulation Methods 0.000 abstract 1
- 238000010998 test method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
Abstract
The application provides a test system of simulation aeroengine oil pump ventilation bearing chamber performance, the system includes: the system comprises a heating lubricating oil tank with an oil-gas separation device, a mixing tank, a motor-driven coaxial oil supply pump, an oil return pump, a heating air source, an adjustable third electromagnetic valve, an adjustable fourth electromagnetic valve, an adjustable second electromagnetic valve, an adjustable first electromagnetic valve and an adjustable atmospheric electromagnetic valve. The application provides a test system can simulate the temperature and the flow of bearing chamber seal bleed air, the temperature and the flow of bearing chamber fuel feeding/oil return, the form of oil pump ventilation, the experimental measurement obtains the flow of oil pump suction oil and gas and the bearing chamber cavity pressure obtains the bearing chamber performance test data of oil pump ventilation, and the test system of this application has simple structure, have commonality and advantage with low costs, can be used for simulating the oil pump ventilation bearing chamber of any structure engine, can obtain the ability law of oil pump suction oil gas and the engine bearing chamber pressure response law of oil pump ventilation through this testing arrangement.
Description
Technical Field
The application belongs to the technical field of aero-engine tests, and particularly relates to a test system and a method for simulating performance of a ventilating bearing cavity of an aero-engine oil pump.
Background
In the prior art, the test capability of a system level and a bearing cavity component level of an aircraft engine lubricating oil system is relatively weak, and even the capability of simulating a bearing cavity performance test is not provided. The ventilation of the oil pump is a ventilation mode of a bearing cavity of the aeroengine, and has important significance for bearing lubrication research. However, the prior art does not have a device which can simply and effectively simulate the working condition of a ventilating bearing cavity system of an engine oil pump.
Disclosure of Invention
It is an object of the present application to provide a test system and method for simulating the performance of an aircraft engine oil pump vent bearing cavity that addresses or mitigates at least one of the problems of the background art.
On one hand, the technical scheme provided by the application is as follows: a test system for simulating performance of an aircraft engine oil pump vent bearing cavity, the system comprising: the system comprises a heating lubricating oil tank with an oil-gas separation device, a mixing tank, a motor-driven coaxial oil supply pump, an oil return pump, a heating gas source, an adjustable third electromagnetic valve, an adjustable fourth electromagnetic valve, an adjustable second electromagnetic valve, an adjustable first electromagnetic valve and an adjustable atmospheric electromagnetic valve;
the oil supply pump is used for simulating the oil supply of flow and pressure corresponding to a bearing cavity of the engine, the oil supply pump pumps out the lubricating oil of the heating lubricating oil tank to flow into the mixing tank, an overflow path with adjustable flow is arranged at the outlet of the oil supply pump, and the lubricating oil of the overflow path flows back to the heating oil tank again;
the mixing box is used for simulating a bearing cavity of an engine and is connected with a heating air source, and the heating air source is used for introducing air with preset flow and temperature into the mixing box and is used for simulating sealing air entraining of the engine; the mixing box is provided with an outlet communicated with the atmosphere;
the oil return pump is used for simulating an engine oil return pump set, and the oil return pump is used for pumping back lubricating oil and air of the mixing box and returning the lubricating oil and the air to the warming oil tank 2 through the oil-gas separation device 1 of the warming oil tank 2;
the heating air source simulates sealed air entraining of the corresponding flow and pressure of the engine and is communicated with the mixing box;
the third electromagnetic valve, the fourth electromagnetic valve, the second electromagnetic valve, the first electromagnetic valve and the atmospheric electromagnetic valve are respectively arranged on a pipeline between the oil supply pump and the mixing box, a pipeline between the oil return pump and the oil-gas separation device, an overflow path between the oil supply pump and the oil-gas separation device, a pipeline between the heating air source and the mixing box and a pipeline between the mixing box and the atmosphere, and the on-off of the corresponding pipelines is adjusted through the electromagnetic valves.
In this application be equipped with oil between lubricating oil tank and the fuel feed pump and strain for the lubricating oil that flows out in the lubricating oil tank that heats filters.
In this application, the motor passes through gear box and adapter and connects the fuel feed pump be equipped with first speedometer on the adapter for measure motor speed.
In this application, be equipped with second manometer and second thermometer on the pipeline between fuel feeding pump and the blending tank for measure the flow and the temperature of this pipeline.
In this application, be equipped with the third manometer on the pipeline between oil return pump and the oil-gas separation device of the tank that heats for measure the flow of this pipeline.
In the application, be equipped with the atmosphere manometer on the pipeline between blending box and the atmosphere for measure the pressure of blending box.
In this application, be equipped with filter screen, flowmeter and first thermometer on the pipeline between air supply and the mixing box of heating for the air of air supply that filters and right the air carries out the measurement of flow and temperature.
On the other hand, the technical scheme provided by the application is as follows: a testing method using a testing system for simulating the performance of a ventilating bearing cavity of an oil pump of an aircraft engine as described in any one of the preceding claims, the testing method comprising:
controlling the electromagnetic valve to open to enable the mixing box to be communicated with the atmosphere;
adjusting the temperature of the heating lubricating oil tank to make the temperature reach the same oil supply temperature of the engine;
starting the motor to enable the rotating speed of the motor to be the same as that of the engine;
adjusting a second electromagnetic valve to enable the flow of the lubricating oil flowing into the mixing box to reach a preset flow;
starting a heating air source, opening a first electromagnetic valve and gradually closing an atmospheric electromagnetic valve, and adjusting the first electromagnetic valve to enable the air flow flowing into the mixing box to be the same as the sealing bleed air flow of the engine;
adjusting the third electromagnetic valve to enable the outlet pressure of the oil supply pump to be the same as the pressure of the engine; adjusting a fourth electromagnetic valve to enable the outlet pressure of the oil return pump to be the same as the pressure of the engine;
keeping the time for a preset time, and recording the pressure value of the blending box.
The application provides a test system can simulate the temperature and the flow of bearing chamber seal bleed air, the temperature and the flow of bearing chamber fuel feeding/oil return, the form of oil pump ventilation, the experimental measurement obtains the flow of oil pump suction oil and gas and the bearing chamber cavity pressure obtains the bearing chamber performance test data of oil pump ventilation, and the test system of this application has simple structure, have commonality and advantage with low costs, can be used for simulating the oil pump ventilation bearing chamber of any structure engine, can obtain the ability law of oil pump suction oil gas and the engine bearing chamber pressure response law of oil pump ventilation through this testing arrangement.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a block diagram of a test system according to the present application.
Reference numerals:
1-oil-gas separation device
2-heating oil tank
3-oil filter
4-electric machine
5-Gear case
6-oil supply pump
7-second pressure gauge
8-third solenoid valve
9-first tachometer
10-fourth solenoid valve
11-third pressure gauge
12-oil return pump
13-second solenoid valve
14-second thermometer
15-mixing box
16-warming air source
17-filter screen
18-first solenoid valve
19-first thermometer
20-atmosphere pressure gauge
21-atmosphere electromagnetic valve
22-adapter
23-flow meter
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 drawings in the embodiments of the present application.
As shown in fig. 1, the test system for simulating the performance of the ventilating bearing cavity of the oil pump of the aircraft engine provided by the application mainly comprises: the system comprises a warming lubricating oil tank 2 with an oil-gas separation device 1, a blending tank 15, a coaxial oil supply pump 6 and an oil return pump 12 driven by a motor 4, a warming air source 16, an adjustable third electromagnetic valve 8, an adjustable fourth electromagnetic valve 10, an adjustable second electromagnetic valve 13, an adjustable first electromagnetic valve 18 and an adjustable atmospheric electromagnetic valve 21; the oil supply pump 6 simulates oil supply of flow and pressure corresponding to an engine bearing cavity, the oil supply pump 6 pumps out lubricating oil of the heating lubricating oil tank 2 and flows into the blending tank 15, in order to ensure that the flow is consistent with the actual oil supply flow of the engine, an overflow path with adjustable flow is arranged at the outlet of the oil supply pump 6, and the lubricating oil of the overflow path flows back to the heating oil tank 2 again; the mixing box 15 is used for simulating a bearing cavity of an engine, the mixing box 15 is connected with a warming air source 16, and the warming air source 16 is used for introducing air with preset flow and temperature into the mixing box 15 and is used for simulating sealing air entraining of the engine; the mixing box 15 is provided with an outlet communicated with the atmosphere; the oil return pump 12 is used for simulating an engine oil return pump set, and the oil return pump 12 is used for pumping back lubricating oil and air in the blending tank 15 and returning the lubricating oil and the air to the warming oil tank 2 through the oil-gas separation device 1 of the warming oil tank 2; the heating air source 16 simulates sealed air entraining of the corresponding flow and pressure of the engine, and the heating air source 16 is communicated with the mixing box 15; the third electromagnetic valve 8, the fourth electromagnetic valve 10, the second electromagnetic valve 13, the first electromagnetic valve 18 and the atmospheric electromagnetic valve 21 are respectively arranged on a pipeline between the oil supply pump 6 and the blending tank 15, a pipeline between the oil return pump 12 and the oil-gas separation device 1, an overflow path between the oil supply pump 6 and the oil-gas separation device 1, a pipeline between the heating air source 16 and the blending tank 15 and a pipeline between the blending tank 15 and the atmosphere, and the on-off of the corresponding pipelines is adjusted through the electromagnetic valves 8,10,13,18 and 21.
In this application be equipped with oil between lubricating oil tank 2 and the fuel feed pump 6 and strain 3 for the lubricating oil that flows out in the lubricating oil tank 2 that heats filters.
In the application, motor 4 passes through gear box 5 and adapter 22 and connects fuel feed pump 6 be equipped with first speedometer 9 on adapter 22 for measure motor speed.
In the application, a second pressure gauge 7 and a second thermometer 14 are arranged on a pipeline between the oil supply pump 6 and the blending tank 15 and used for measuring the flow and the temperature of the pipeline.
In the application, a third pressure gauge 11 is arranged on a pipeline between the oil return pump 12 and the oil-gas separation device 1 of the warming lubricating oil tank 2 and used for measuring the flow of the pipeline.
In the present application, an atmosphere pressure gauge 20 is arranged on a pipeline between the blending box 15 and the atmosphere and used for measuring the pressure of the blending box 15.
In this application, be equipped with filter screen 17, flowmeter 23 and first thermometer on the pipeline between warming air supply 16 and blending box 15 for the air of filtering warming air supply 16 and to the measurement of flow and temperature is carried out to the air.
In addition, the application also provides a test method of the test system for simulating the performance of the ventilating bearing cavity of the oil pump of the aircraft engine, wherein the test method comprises the following steps:
1) controlling the electromagnetic valve 21 to be opened to enable the blending box 15 to be communicated with the atmosphere;
2) adjusting the temperature of the heating lubricating oil tank 2 to make the temperature reach the same oil supply temperature of the engine;
3) starting the motor 4 to enable the rotating speed of the motor 4 to be the same as that of the engine;
4) adjusting the second electromagnetic valve 13 to make the flow of the lubricating oil flowing into the blending box 15 reach the preset flow;
5) starting a warming air source 16, opening a first electromagnetic valve 18 and gradually closing an atmospheric electromagnetic valve 21, and adjusting the first electromagnetic valve 18 to enable the air flow flowing into the mixing box 15 to be the same as the engine sealing bleed air flow;
6) adjusting the third electromagnetic valve 8 to enable the outlet pressure of the oil supply pump to be the same as the pressure of the engine; adjusting the fourth electromagnetic valve 10 to make the outlet pressure of the oil return pump 12 the same as the pressure of the engine;
7) the predetermined time is maintained and the pressure value of the blender box 15 (measured by the atmospheric pressure gauge 20) is recorded. In an embodiment of the present application, the holding time may be set to 2 Min.
The application provides a test system can simulate the temperature and the flow of bearing chamber seal bleed air, the temperature and the flow of bearing chamber fuel feeding/oil return, the form of oil pump ventilation, the experimental measurement obtains the flow of oil pump suction oil and gas and the bearing chamber cavity pressure obtains the bearing chamber performance test data of oil pump ventilation, and the test system of this application has simple structure, have commonality and advantage with low costs, can be used for simulating the oil pump ventilation bearing chamber of any structure engine, can obtain the ability law of oil pump suction oil gas and the engine bearing chamber pressure response law of oil pump ventilation through this testing arrangement.
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 (8)
1. A test system for simulating the performance of a ventilating bearing cavity of an oil pump of an aircraft engine, the system comprising: the system comprises a heating lubricating oil tank (2) with an oil-gas separation device (1), a blending tank (15), a coaxial oil supply pump (6) and an oil return pump (12) driven by a motor (4), a heating air source (16), an adjustable third electromagnetic valve (8), a fourth electromagnetic valve (10), a second electromagnetic valve (13), a first electromagnetic valve (18) and an atmospheric electromagnetic valve (21);
the oil supply pump (6) simulates oil supply of flow and pressure corresponding to an engine bearing cavity, the oil supply pump (6) pumps out lubricating oil of the heating lubricating oil tank (2) to flow into the blending tank (15), an overflow path with adjustable flow is arranged at the outlet of the oil supply pump (6), and the lubricating oil of the overflow path flows back to the heating oil tank (2) again;
the mixing box (15) is used for simulating a bearing cavity of an engine, the mixing box (15) is connected with a heating air source (16), and the heating air source (16) is used for introducing air with preset flow and temperature into the mixing box (15) and is used for simulating sealed air-entraining of the engine; the mixing box (15) is provided with an outlet communicated with the atmosphere;
the oil return pump (12) is used for simulating an engine oil return pump set, and the oil return pump (12) is used for pumping the lubricating oil and the air in the blending tank (15) back to the warming oil tank 2 through the oil-gas separation device 1 of the warming oil tank 2;
the heating air source (16) simulates sealed air entraining of the corresponding flow and pressure of the engine, and the heating air source (16) is communicated with the mixing box (15);
the third electromagnetic valve (8), the fourth electromagnetic valve (10), the second electromagnetic valve (13), the first electromagnetic valve (18) and the atmosphere electromagnetic valve (21) are respectively arranged on a pipeline between the oil supply pump (6) and the blending tank (15), a pipeline between the oil return pump (12) and the oil-gas separation device (1), an overflow path between the oil supply pump (6) and the oil-gas separation device (1), a pipeline between the heating air source (16) and the blending tank (15) and a pipeline between the blending tank (15) and the atmosphere, and the on-off of the corresponding pipelines is adjusted through the electromagnetic valves (8,10,13,18 and 21).
2. A test system for simulating the performance of a ventilation bearing cavity of an oil pump of an aircraft engine according to claim 1, characterized in that an oil filter (3) is arranged between the warmed lubricating oil tank (2) and the oil supply pump (6) for filtering lubricating oil flowing out of the warmed lubricating oil tank (2).
3. The test system for simulating the performance of the ventilating bearing cavity of the oil pump of the aircraft engine is characterized in that the motor (4) is connected with the oil supply pump (6) through the gear box (5) and the adapter (22), and the first tachometer (9) is arranged on the adapter (22) and used for measuring the rotating speed of the motor.
4. A test system for simulating the performance of a ventilation bearing cavity of an oil pump of an aircraft engine according to claim 1, characterized in that a second pressure gauge (7) and a second temperature gauge (14) are arranged on a pipeline between the oil supply pump (6) and the blending tank (15) and used for measuring the flow rate and the temperature of the pipeline.
5. The test system for simulating the performance of the ventilating bearing cavity of the oil pump of the aircraft engine is characterized in that a third pressure gauge (11) is arranged on a pipeline between the oil return pump (12) and the oil-gas separation device (1) of the warming lubricating oil tank (2) and used for measuring the flow of the pipeline.
6. The test system for simulating the performance of the ventilating bearing cavity of the oil pump of the aircraft engine is characterized in that an atmospheric pressure gauge (20) is arranged on a pipeline between the blending box (15) and the atmosphere and used for measuring the pressure of the blending box (15).
7. The test system for simulating the performance of the ventilating bearing cavity of the oil pump of the aircraft engine according to claim 1, wherein a filter screen (17), a flow meter (23) and a first temperature gauge are arranged on a pipeline between the warming air source (16) and the blending tank (15) and are used for filtering the air of the warming air source (16) and measuring the flow rate and the temperature of the air.
8. A testing method using a testing system for simulating the performance of a ventilating bearing cavity of an oil pump of an aircraft engine according to any one of claims 1 to 7, wherein the testing method comprises the following steps:
controlling the electromagnetic valve (21) to be opened to enable the blending box (15) to be communicated with the atmosphere;
the temperature of the heating lubricating oil tank (2) is adjusted to reach the same oil supply temperature of the engine;
starting the motor (4) to enable the rotating speed of the motor (4) to be the same as that of the engine;
adjusting a second electromagnetic valve (13) to enable the flow of the lubricating oil flowing into the blending box (15) to reach a preset flow;
starting a warming air source (16), opening a first electromagnetic valve (18) and gradually closing an atmospheric electromagnetic valve (21), and adjusting the first electromagnetic valve (18) to enable the air flow flowing into the blending box (15) to be the same as the sealing bleed air flow of the engine;
adjusting a third electromagnetic valve (8) to enable the outlet pressure of the oil supply pump to be the same as the pressure of the engine; adjusting a fourth electromagnetic valve (10) to enable the outlet pressure of the oil return pump (12) to be the same as the pressure of the engine;
keeping for a predetermined time, and recording the pressure value of the blending tank (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011192233.8A CN112254971A (en) | 2020-10-30 | 2020-10-30 | Test system and method for simulating performance of ventilating bearing cavity of oil pump of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011192233.8A CN112254971A (en) | 2020-10-30 | 2020-10-30 | Test system and method for simulating performance of ventilating bearing cavity of oil pump of aircraft engine |
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| CN112254971A true CN112254971A (en) | 2021-01-22 |
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| CN202011192233.8A Pending CN112254971A (en) | 2020-10-30 | 2020-10-30 | Test system and method for simulating performance of ventilating bearing cavity of oil pump of aircraft engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113378320A (en) * | 2021-06-25 | 2021-09-10 | 中国航发沈阳发动机研究所 | Method and device for determining temperature of lubricating oil cavity |
| CN113790889A (en) * | 2021-08-10 | 2021-12-14 | 哈尔滨工业大学 | Engine experiment table bearing lubricating oil thermal cycle measurement system |
| CN114215624A (en) * | 2021-11-29 | 2022-03-22 | 中国航发沈阳发动机研究所 | Oil supply throttling device for cold running of engine and starting before starter is disengaged |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113378320A (en) * | 2021-06-25 | 2021-09-10 | 中国航发沈阳发动机研究所 | Method and device for determining temperature of lubricating oil cavity |
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| CN113790889A (en) * | 2021-08-10 | 2021-12-14 | 哈尔滨工业大学 | Engine experiment table bearing lubricating oil thermal cycle measurement system |
| CN114215624A (en) * | 2021-11-29 | 2022-03-22 | 中国航发沈阳发动机研究所 | Oil supply throttling device for cold running of engine and starting before starter is disengaged |
| CN114215624B (en) * | 2021-11-29 | 2023-02-28 | 中国航发沈阳发动机研究所 | Oil supply throttling device for cold running of engine and starting before starter is disengaged |
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Application publication date: 20210122 |
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