CN202926581U - Test system for main fuel pump of airplane - Google Patents
Test system for main fuel pump of airplane Download PDFInfo
- Publication number
- CN202926581U CN202926581U CN 201220612959 CN201220612959U CN202926581U CN 202926581 U CN202926581 U CN 202926581U CN 201220612959 CN201220612959 CN 201220612959 CN 201220612959 U CN201220612959 U CN 201220612959U CN 202926581 U CN202926581 U CN 202926581U
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- pressure
- fuel pump
- main fuel
- oil
- pipeline
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Abstract
The utility model discloses a test system for a main fuel pump of an airplane. The test system comprises an oil supply unit used for providing oil for a tested main fuel pump and an oil drainage loading test unit used for simulating the performance test of the main fuel pump under airplane load, wherein the oil supply unit is connected with the tested main fuel pump; and the oil drainage loading test unit is connected with the tested main fuel pump to form a closed loop. The test system disclosed by the utility model has the advantages of simple structure, high safety, good test effect, high working efficiency and long service life.
Description
Technical field
The utility model relates to the hydraulic air field tests, is specially a kind of Aircraft Main fuel pump test system.
Background technique
The Aircraft Main fuel pump is driven by accessory drive casing, and its effect is that the fuel oil of certain pressure, flow and temperature is provided to airplane engine, guarantee normal working of engine, so the reliability of main fuel pump is most important, directly concerns the flight safety of aircraft.But Aircraft Main fuel pump test system at present on the market can not be used for the testing property of the main fuel pump of active service main flow commercial engines, be difficult to guarantee that before the main fuel pump installation be that safety is available, therefore research and develop safely, time and tide wait for no man for the Aircraft Main fuel pump test system of good test effect.
The model utility content
The purpose of this utility model is in order to overcome above-mentioned the deficiencies in the prior art part, and a kind of simple in structure, Aircraft Main fuel pump test system that test is accurate, safe is provided.
The purpose of this utility model reaches by following measure: Aircraft Main fuel pump test system, it comprises for the oil supply unit that fuel oil is provided to tested main fuel pump and is used for simulating the oil extraction loading test cell of the testing property of main fuel pump under the aircraft load, described oil supply unit is connected with tested main fuel pump, and described oil extraction loading test cell is connected with tested main fuel pump and forms the closed-loop path.
In technique scheme, described oil supply unit comprises fuel tank, be connected with suction booster, cooler in turn, supply oil strainer, oil temperature supplying sensor and charge oil pressure sensor by pipeline on described fuel tank, described charge oil pressure sensor is connected with tested main fuel pump, be provided with fuel feeding by-pass throttle valve by pipeline between described oil temperature supplying sensor and charge oil pressure sensor, described fuel feeding by-pass throttle valve is connected with fuel tank by pipeline.
In technique scheme, described oil extraction loads test cell and comprises back pressure valve, oil extraction flowmeter, draining oil filter, outlet temperature sensor and the outlet pressure sensor that connects successively by pipeline, described back pressure valve is connected with fuel tank, described outlet pressure sensor is connected with tested main fuel pump by pipeline, be connected with ball valve, flowmeter, throttle valve and pressure transducer in turn by pipeline between described back pressure valve and oil extraction flowmeter, described pressure transducer is connected by the tested main fuel pump of pipeline.
In technique scheme, also comprise the Pressure Drop test cell, described Pressure Drop test cell comprises differential pressure transducer and differential pressure throttle valve, and described differential pressure transducer is in parallel by pipeline with the differential pressure throttle valve, and the two ends of described differential pressure transducer are connected with tested main fuel pump by pipeline.
In technique scheme, also comprise pressure measuring unit, described pressure measuring unit comprises the first pressure measurement pressure gauge, the second pressure measurement pressure gauge and the 3rd pressure measurement pressure gauge, and described the first pressure measurement pressure gauge, the second pressure measurement pressure gauge and the 3rd pressure measurement pressure gauge are connected with tested main fuel pump respectively.
In technique scheme, described oil supply unit also comprises the fuel feeding ball valve, and described fuel feeding ball valve is arranged between described oil temperature supplying sensor and charge oil pressure sensor, and described fuel feeding by-pass throttle valve is arranged between fuel feeding ball valve and charge oil pressure sensor.
In technique scheme, also be provided with visual level meter and liquid level sensor on described fuel tank.
In technique scheme, also be provided with fuel outlet valve on described fuel tank.
The utility model is simple in structure, not only safe and also the test effect might as well, in addition, the utility model high working efficiency, long service life.
Description of drawings
Fig. 1 is the whole theory diagram of the utility model.
Fig. 2 is the utility model hydraulic schematic diagram.
101. oil supply units in figure, 201. oil extraction loads test cell, 301. Pressure Drop test cell, 401. pressure measuring unit, 1. fuel tank, 2. suction booster, 3. cooler, 4. for oil strainer, 5. oil temperature supplying sensor, 6. fuel feeding ball valve, 7. charge oil pressure sensor, 8. outlet temperature sensor, 9. outlet pressure sensor, 10. the 3rd pressure measurement pressure gauge, 11. the second pressure measurement pressure gauge, 12. the first pressure measurement pressure gauge, 13. differential pressure transducer, 14. pressure transducer, 15. differential pressure throttle valve, 16. throttle valve, 17. draining oil filter, 18. flowmeter, 19. ball valve, 20. oil extraction flowmeter, 21. fuel feeding by-pass throttle valve, 22. back pressure valve, 23. fuel outlet valve, 24. visual level meter, 25. liquid level sensor.
Embodiment
Describe performance of the present utility model in detail below in conjunction with accompanying drawing, but they do not consist of to restriction of the present utility model, only for example, simultaneously by illustrating that advantage of the present utility model will become more clear and easily understand.
Consult accompanying drawing as can be known: the utility model Aircraft Main fuel pump test system, it comprises for the oil supply unit 101 that fuel oil is provided to tested main fuel pump, loads test cell 201 for the simulation main fuel pump in the oil extraction of the testing property under the aircraft load, is used for the monitoring main fuel pump connects the Pressure Drop test cell 301 of Pressure Drop that heat exchanger produces and is used for test main fuel pump pressure port pressure when installing pressure measuring unit 401.Oil supply unit 101, pressure measuring unit 401 are connected with tested main fuel pump, and oil extraction loading test cell 201 is connected with tested main fuel pump respectively with Pressure Drop test cell 301 and forms closed-loop path (as shown in Figure 1 and Figure 2).
Oil extraction loads test cell 201 and comprises back pressure valve 22, oil extraction flowmeter 20, draining oil filter 17, outlet temperature sensor 8 and the outlet pressure sensor 9 that connects successively by pipeline, described back pressure valve 22 is connected with fuel tank 1, described outlet pressure sensor 9 is connected with tested main fuel pump by pipeline, be connected with ball valve 19, flowmeter 18, throttle valve 16 and pressure transducer 14 in turn by pipeline between described back pressure valve 22 and oil extraction flowmeter 20, described pressure transducer 14 is connected by the tested main fuel pump of pipeline.oil extraction loads the testing property under specified loads aboard of the main simulation main fuel pump of test cell 201, the high pressure fuel of tested main combustion pump output filters through draining oil filter 17, whether met the requirements by oil extraction flowmeter 20 its output flows of test, the fuel oil of oil extraction flowmeter 20 of flowing through is divided into two-way, lead up to back pressure valve 22 oil sump tanks 1, control the outlet load by back pressure valve 22, thereby simulation is at installation state load test, main fuel pump is returned on another road, controlled the break-make in its loop by ball valve 19, flowmeter 18 is measured the size of fuel oil return flow, throttle valve 16 is regulated the size of returning to fuel flow.Outlet oil temperature and pressure return to the pressure of fuel oil by pressure transducer 14 monitorings respectively by outlet temperature sensor 8 outlet pressure sensor 9 monitorings.
Pressure Drop test cell 301 comprises differential pressure transducer 13 and differential pressure throttle valve 15, and described differential pressure transducer 13 is in parallel by pipeline with differential pressure throttle valve 15, and the two ends of described differential pressure transducer 13 are connected with tested main fuel pump by pipeline.Replace main fuel pump to connect the Pressure Drop that heat exchanger produces when installing by regulating differential pressure throttle valve 15, its Pressure Drop is by differential pressure transducer 13 monitorings.
Claims (8)
1. Aircraft Main fuel pump test system, it is characterized in that: comprise for the oil supply unit (101) that fuel oil is provided to tested main fuel pump with for the oil extraction of simulating the testing property of main fuel pump under the aircraft load loading test cell (201), described oil supply unit (101) is connected with tested main fuel pump, and described oil extraction loading test cell (201) is connected with tested main fuel pump and forms the closed-loop path.
2. Aircraft Main fuel pump test system according to claim 1, it is characterized in that described oil supply unit (101) comprises fuel tank (1), described fuel tank (1) is upper is connected with suction booster (2) in turn by pipeline, cooler (3), for oil strainer (4), oil temperature supplying sensor (5) and charge oil pressure sensor (7), described charge oil pressure sensor (7) is connected with tested main fuel pump, be provided with fuel feeding by-pass throttle valve (21) by pipeline between described oil temperature supplying sensor (5) and charge oil pressure sensor (7), described fuel feeding by-pass throttle valve (21) is connected with fuel tank (1) by pipeline.
3. Aircraft Main fuel pump test system according to claim 1 and 2, it is characterized in that described oil extraction loads test cell (201) and comprises the back pressure valve (22) that connects successively by pipeline, oil extraction flowmeter (20), draining oil filter (17), outlet temperature sensor (8) and outlet pressure sensor (9), described back pressure valve (22) is connected with fuel tank (1), described outlet pressure sensor (9) is connected with tested main fuel pump by pipeline, be connected with ball valve (19) in turn by pipeline between described back pressure valve (22) and oil extraction flowmeter (20), flowmeter (18), throttle valve (16) and pressure transducer (14), described pressure transducer (14) is connected by the tested main fuel pump of pipeline.
4. Aircraft Main fuel pump test system according to claim 1 and 2, characterized by further comprising Pressure Drop test cell (301), described Pressure Drop test cell (301) comprises differential pressure transducer (13) and differential pressure throttle valve (15), described differential pressure transducer (13) is in parallel by pipeline with differential pressure throttle valve (15), and the two ends of described differential pressure transducer (13) are connected with tested main fuel pump by pipeline.
5. Aircraft Main fuel pump test system according to claim 1 and 2, characterized by further comprising pressure measuring unit (401), described pressure measuring unit (401) comprises the first pressure measurement pressure gauge (12), the second pressure measurement pressure gauge (11) and the 3rd pressure measurement pressure gauge (10), and described the first pressure measurement pressure gauge (12), the second pressure measurement pressure gauge (11) and the 3rd pressure measurement pressure gauge (10) are connected with tested main fuel pump respectively.
6. Aircraft Main fuel pump test system according to claim 1 and 2, it is characterized in that described oil supply unit (101) also comprises fuel feeding ball valve (6), described fuel feeding ball valve (6) is arranged between described oil temperature supplying sensor (5) and charge oil pressure sensor (7), and described fuel feeding by-pass throttle valve (21) is arranged between fuel feeding ball valve (6) and charge oil pressure sensor (7).
7. Aircraft Main fuel pump test system according to claim 2, is characterized in that also being provided with on described fuel tank (1) visual level meter (24) and liquid level sensor (25).
8. Aircraft Main fuel pump test system according to claim 2, is characterized in that also being provided with on described fuel tank (1) fuel outlet valve (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220612959 CN202926581U (en) | 2012-11-19 | 2012-11-19 | Test system for main fuel pump of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220612959 CN202926581U (en) | 2012-11-19 | 2012-11-19 | Test system for main fuel pump of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202926581U true CN202926581U (en) | 2013-05-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220612959 Expired - Fee Related CN202926581U (en) | 2012-11-19 | 2012-11-19 | Test system for main fuel pump of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202926581U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102996426A (en) * | 2012-11-19 | 2013-03-27 | 武汉航达航空科技发展有限公司 | Test system for main fuel pump of airplane |
| CN107956621A (en) * | 2017-12-12 | 2018-04-24 | 成都航利电气有限公司 | A kind of main fuel pump performance test device |
| CN109367809A (en) * | 2018-08-16 | 2019-02-22 | 广州飞机维修工程有限公司 | Interplane fuel oil delivery method and its equipment |
-
2012
- 2012-11-19 CN CN 201220612959 patent/CN202926581U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102996426A (en) * | 2012-11-19 | 2013-03-27 | 武汉航达航空科技发展有限公司 | Test system for main fuel pump of airplane |
| CN102996426B (en) * | 2012-11-19 | 2015-08-26 | 武汉航达航空科技发展有限公司 | Test system for main fuel pump of airplane |
| CN107956621A (en) * | 2017-12-12 | 2018-04-24 | 成都航利电气有限公司 | A kind of main fuel pump performance test device |
| CN109367809A (en) * | 2018-08-16 | 2019-02-22 | 广州飞机维修工程有限公司 | Interplane fuel oil delivery method and its equipment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130508 Termination date: 20171119 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |