CN102996426A - Test system for main fuel pump of airplane - Google Patents
Test system for main fuel pump of airplane Download PDFInfo
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- CN102996426A CN102996426A CN2012104677712A CN201210467771A CN102996426A CN 102996426 A CN102996426 A CN 102996426A CN 2012104677712 A CN2012104677712 A CN 2012104677712A CN 201210467771 A CN201210467771 A CN 201210467771A CN 102996426 A CN102996426 A CN 102996426A
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Abstract
The invention discloses a test system for a main fuel pump of an airplane. The test system for the main fuel pump of the airplane comprises a fuel supply unit which supplies fuel to a main fuel pump to be tested and a fuel discharge loading test unit which simulates a performance test of the main fuel pump under the condition that the airplane is loaded, wherein the fuel supply unit is connected with the main fuel pump to be tested, and the fuel discharge loading test unit is connected with the main fuel pump to be tested to form a closed loop. The test system for the main fuel pump of the airplane has the advantages of simple structure, high safety and good test effect, and the test system for the main fuel pump of the airplane is high in working efficiency and long in service life.
Description
Technical field
The present invention relates to the hydraulic air field tests, be 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 the fuel oil that certain pressure, flow and temperature are provided to airplane engine, guarantees 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.
Summary of the invention
The objective of the invention 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 objective of the invention is to reach 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 links to each other with tested main fuel pump, and described oil extraction loading test cell links to each other 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 the described fuel tank, described charge oil pressure sensor links to each other with tested main fuel pump, be provided with fuel feeding by-pass throttle valve by pipeline between described oil temperature supplying sensor and the charge oil pressure sensor, described fuel feeding by-pass throttle valve links to each other 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 links to each other with fuel tank, described outlet pressure sensor links to each other 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 the oil extraction flowmeter, described pressure transducer links to each other 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 link to each other 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 link to each other 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 the charge oil pressure sensor, and described fuel feeding by-pass throttle valve is arranged between fuel feeding ball valve and the charge oil pressure sensor.
In technique scheme, also be provided with visual level meter and liquid level sensor on the described fuel tank.
In technique scheme, also be provided with fuel outlet valve on the described fuel tank.
The present invention is simple in structure, not only safe and also the test effect might as well, in addition, high working efficiency of the present invention, long service life.
Description of drawings
Fig. 1 is the whole theory diagram of the present invention.
Fig. 2 is hydraulic schematic diagram of the present invention.
101. oil supply units among the figure, 201. oil extractions load test cell, 301. Pressure Drop test cells, 401. pressure measuring unit, 1. fuel tank, 2. suction booster, 3. cooler 4. supplies 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. second pressure measurement pressure gauges, 12. the first pressure measurement pressure gauge, 13. differential pressure transducer, 14. pressure transducers, 15. differential pressure throttle valves, 16. throttle valve, 17. draining oil filter, 18. flowmeters, 19. ball valves, 20. oil extraction flowmeter, 21. fuel feeding by-pass throttle valve, 22. back pressure valves, 23. fuel outlet valves, 24. visual level meter, 25. liquid level sensors.
Embodiment
Describe performance of the present invention in detail below in conjunction with accompanying drawing, but they do not consist of limitation of the invention, only for example, simultaneously by illustrating that advantage of the present invention will become more clear and easily understanding.
Consult accompanying drawing as can be known: Aircraft Main fuel pump test system of the present invention, it comprises for the oil supply unit 101 that fuel oil is provided to tested main fuel pump, loads test cell 201 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 for the simulation main fuel pump.Oil supply unit 101, pressure measuring unit 401 link to each other with tested main fuel pump, and oil extraction loading test cell 201 links to each other 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 links to each other with fuel tank 1, described outlet pressure sensor 9 links to each other 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 the oil extraction flowmeter 20, described pressure transducer 14 links to each other by the tested main fuel pump of pipeline.Oil extraction loads the aboard testing property under the specified loads of test cell 201 main simulation main fuel pumps, 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, by back pressure valve 22 control outlet loads, thereby simulation is at installation state load test, main fuel pump is returned on another road, break-make by ball valve 19 its loops of control, flowmeter 18 is measured the size of fuel oil return flow, and throttle valve 16 is regulated the size of returning fuel flow.Outlet oil temperature and pressure return the pressure of fuel oil by pressure transducer 14 monitorings respectively by 9 monitorings of outlet temperature sensor 8 outlet pressure sensors.
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 link to each other 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) links to each other with tested main fuel pump, and described oil extraction loading test cell (201) links to each other 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 to be 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) links to each other 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 the charge oil pressure sensor (7), described fuel feeding by-pass throttle valve (21) links to each other 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) links to each other with fuel tank (1), described outlet pressure sensor (9) links to each other with tested main fuel pump by pipeline, be connected with ball valve (19) in turn by pipeline between described back pressure valve (22) and the oil extraction flowmeter (20), flowmeter (18), throttle valve (16) and pressure transducer (14), described pressure transducer (14) links to each other 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) link to each other 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) link to each other 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 the charge oil pressure sensor (7), and described fuel feeding by-pass throttle valve (21) is arranged between fuel feeding ball valve (6) and the 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 the 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 the described fuel tank (1) fuel outlet valve (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210467771.2A CN102996426B (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 |
|---|---|---|---|
| CN201210467771.2A CN102996426B (en) | 2012-11-19 | 2012-11-19 | Test system for main fuel pump of airplane |
Publications (2)
| Publication Number | Publication Date |
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| CN102996426A true CN102996426A (en) | 2013-03-27 |
| CN102996426B CN102996426B (en) | 2015-08-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210467771.2A Expired - Fee Related CN102996426B (en) | 2012-11-19 | 2012-11-19 | Test system for main fuel pump of airplane |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104500505A (en) * | 2014-12-19 | 2015-04-08 | 上海电气液压气动有限公司 | Impact test system for open hydraulic pump |
| CN104931266A (en) * | 2015-06-02 | 2015-09-23 | 中航飞机股份有限公司西安飞机分公司 | Aircraft engine fuel oil simulation control system and adjusting method |
| CN105258948A (en) * | 2015-11-28 | 2016-01-20 | 南通华夏飞机工程技术股份有限公司 | Aviation fuel adjusting and testing system |
| CN105486510A (en) * | 2015-11-28 | 2016-04-13 | 南通华夏飞机工程技术股份有限公司 | Fuel regulation test operation desk |
| CN106124189A (en) * | 2016-08-29 | 2016-11-16 | 中国人民解放军空军第航空学院 | Novel emergency oil pump detection device |
| CN110207991A (en) * | 2019-06-25 | 2019-09-06 | 哈尔滨工程大学 | Cooling oil duct Oscillation Flows visual Simulation device in crosshead diesel engine piston |
| CN115030891A (en) * | 2022-08-08 | 2022-09-09 | 西安成立航空制造有限公司 | Test platform and test method for fuel pump of aircraft engine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109577923B (en) * | 2018-12-03 | 2021-06-25 | 重庆大学 | Device for measuring backflow amount during coal bed gas mining test |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104500505A (en) * | 2014-12-19 | 2015-04-08 | 上海电气液压气动有限公司 | Impact test system for open hydraulic pump |
| CN104931266A (en) * | 2015-06-02 | 2015-09-23 | 中航飞机股份有限公司西安飞机分公司 | Aircraft engine fuel oil simulation control system and adjusting method |
| CN104931266B (en) * | 2015-06-02 | 2018-07-24 | 中航飞机股份有限公司西安飞机分公司 | A kind of airplane engine fuel oil analog control system and adjusting method |
| CN105258948A (en) * | 2015-11-28 | 2016-01-20 | 南通华夏飞机工程技术股份有限公司 | Aviation fuel adjusting and testing system |
| CN105486510A (en) * | 2015-11-28 | 2016-04-13 | 南通华夏飞机工程技术股份有限公司 | Fuel regulation test operation desk |
| CN106124189A (en) * | 2016-08-29 | 2016-11-16 | 中国人民解放军空军第航空学院 | Novel emergency oil pump detection device |
| CN110207991A (en) * | 2019-06-25 | 2019-09-06 | 哈尔滨工程大学 | Cooling oil duct Oscillation Flows visual Simulation device in crosshead diesel engine piston |
| CN115030891A (en) * | 2022-08-08 | 2022-09-09 | 西安成立航空制造有限公司 | Test platform and test method for fuel pump of aircraft engine |
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| CN102996426B (en) | 2015-08-26 |
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Granted publication date: 20150826 Termination date: 20191119 |