CN102996426B - Test system for main fuel pump of airplane - Google Patents
Test system for main fuel pump of airplane Download PDFInfo
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- CN102996426B CN102996426B CN201210467771.2A CN201210467771A CN102996426B CN 102996426 B CN102996426 B CN 102996426B CN 201210467771 A CN201210467771 A CN 201210467771A CN 102996426 B CN102996426 B CN 102996426B
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- pressure
- oil
- fuel pump
- main fuel
- pipeline
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Abstract
The invention discloses a kind of test system for main fuel pump of airplane, it comprises for providing the oil supply unit of fuel oil and the oil extraction for simulating the testing property of main fuel pump under airplane load to load test cell to tested main fuel pump, described oil supply unit is connected with tested main fuel pump, and described oil extraction loads test cell and tested main fuel pump is connected to form closed-loop path.Advantage of the present invention is that structure is simple, not only high the but also test effect of Security might as well, in addition, working efficiency of the present invention is high, long service life.
Description
Technical field
The present invention relates to hydraulic air field tests, be specially a kind of test system for main fuel pump of airplane.
Background technique
Main fuel pump of airplane is driven by accessory drive casing, and its effect is the fuel oil providing certain pressure, flow and temperature to airplane engine, and guarantee normal working of engine, therefore the reliability of main fuel pump is most important, directly concerns the flight safety of aircraft.But test system for main fuel pump of airplane 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, that safety is available before being difficult to guarantee main fuel pump installation, therefore research and develop Security high, time and tide wait for no man for the test system for main fuel pump of airplane of good test effect.
Summary of the invention
The object of the invention is to overcome above-mentioned the deficiencies in the prior art part, and the test system for main fuel pump of airplane that a kind of structure is simple, test is accurate, Security is high is provided.
The object of the invention is to be reached by following measure: test system for main fuel pump of airplane, it comprises for providing the oil supply unit of fuel oil and the oil extraction for simulating the testing property of main fuel pump under airplane load to load test cell to tested main fuel pump, described oil supply unit is connected with tested main fuel pump, and described oil extraction loads test cell and tested main fuel pump is connected to form closed-loop path.
In technique scheme, described oil supply unit comprises fuel tank, described fuel tank is connected with in turn suction booster, cooler by pipeline, is supplied oil strainer, oil temperature supplying sensor and charge oil pressure sensor, 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 is loaded test cell and comprises the back pressure valve, oil extraction flowmeter, draining oil filter, outlet temperature sensor and the outlet pressure sensor that are connected 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 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 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 first pressure measurement pressure gauge, the second pressure measurement pressure gauge are connected with tested main fuel pump respectively with the 3rd pressure measurement pressure gauge.
In technique scheme, described oil supply unit also comprises 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, described fuel tank is also provided with visual liquid-level meter and liquid level sensor.
In technique scheme, described fuel tank is also provided with fuel outlet valve.
Structure of the present invention is simple, not only high the but also test effect of Security might as well, in addition, working efficiency of the present invention is high, long service life.
Accompanying drawing explanation
Fig. 1 is the overall theory diagram of the present invention.
Fig. 2 is hydraulic schematic diagram of the present invention.
101. oil supply units in 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. 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. second pressure measurement pressure gauges, 12. first pressure measurement pressure gauges, 13. differential pressure transducers, 14. pressure transducers, 15. differential pressure throttle valves, 16. throttle valve, 17. draining oil filters, 18. flowmeters, 19. ball valves, 20. oil extraction flowmeters, 21. fuel feeding by-pass throttle valves, 22. back pressure valves, 23. fuel outlet valves, 24. visual liquid-level meters, 25. liquid level sensors.
Embodiment
Describe performance of the present invention in detail below in conjunction with accompanying drawing, but they do not form limitation of the invention, only for example, simultaneously by illustrating that advantage of the present invention will become clearly and easy understand.
Accompanying drawings is known: test system for main fuel pump of airplane of the present invention, it comprise for provide to tested main fuel pump the oil supply unit 101 of fuel oil, for simulate the testing property of main fuel pump under airplane load oil extraction load test cell 201, for monitor main fuel pump install time connect heat exchanger produce the Pressure Drop test cell 301 of Pressure Drop and the pressure measuring unit 401 for testing main fuel pump pressure port pressure.Oil supply unit 101, pressure measuring unit 401 are connected with tested main fuel pump, and oil extraction loads test cell 201 and Pressure Drop test cell 301 is connected to form closed-loop path (as shown in Figure 1 and Figure 2) with tested main fuel pump respectively.
Oil supply unit 101 comprises the fuel tank 1 being provided with fuel outlet valve 23, visual liquid-level meter 24 and liquid level sensor 25, fuel tank 1 is connected with in turn suction booster 2, cooler 3 by pipeline, is supplied oil strainer 4, oil temperature supplying sensor 5, fuel feeding ball valve 6 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 fuel feeding ball valve 6, described fuel feeding by-pass throttle valve 21 is connected with fuel tank 1 by pipeline.Oil supply loop is mainly main fuel pump provides pressure, flow, turbidity test, temperature all satisfactory fuel oil.Visual liquid-level meter 24 and liquid level sensor 25 are for observing and monitoring the height of fuel tank 1 liquid level, and the fuel oil being stored in fuel tank 1, by suction booster 2 supercharging, cools through cooler 3 and filters for oil strainer 4 and enter main fuel pump.Oil temperature supplying sensor 5 and cooling water flow control can realize automatically controlling oil temperature.By regulating the openings of sizes of fuel feeding by-pass throttle valve 21 to control charge oil pressure, monitor its pressure by charge oil pressure sensor 7.Fuel feeding ball valve 6 is automatically closed after off-test, prevents the fluid in fuel tank 1 from outflowing, can open fuel outlet valve 23 and be put totally by oil when needing to safeguard.
Oil extraction is loaded test cell 201 and comprises the back pressure valve 22, oil extraction flowmeter 20, draining oil filter 17, outlet temperature sensor 8 and the outlet pressure sensor 9 that are connected 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 of test cell 201 main analog main fuel pump aboard under specified loads, the high pressure fuel that tested main combustion pump exports filters through draining oil filter 17, test its output flow by oil extraction flowmeter 20 whether to meet the requirements, the fuel oil flowing through oil extraction flowmeter 20 is divided into two-way, lead up to back pressure valve 22 oil sump tank 1, controlled to export load by back pressure valve 22, thus simulation is in the test of installation state load, another road returns main fuel pump, the break-make in its loop is controlled by ball valve 19, the size of fuel oil return flow measured by flowmeter 18, throttle valve 16 regulates the size returning fuel flow.Export oily moderate pressure to be monitored by outlet temperature sensor 8 outlet pressure sensor 9 respectively, the pressure returning fuel oil is monitored by pressure transducer 14.
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.By regulating differential pressure throttle valve 15 to replace the main fuel pump Pressure Drop that connection heat exchanger produces when installing, its Pressure Drop is monitored by differential pressure transducer 13.
Pressure measuring unit 401 comprises the first pressure measurement pressure gauge 12, second pressure measurement pressure gauge 11 and the 3rd pressure measurement pressure gauge 10, and described first pressure measurement pressure gauge 12, second pressure measurement pressure gauge 11 is connected with tested main fuel pump respectively with the 3rd pressure measurement pressure gauge 10.Pressure measuring unit 401 is for testing main fuel pump pressure port pressure.(as shown in Figure 1 and Figure 2).
Claims (1)
1. test system for main fuel pump of airplane, it is characterized in that: comprise for providing the oil supply unit of fuel oil (101) and the oil extraction for simulating the testing property of main fuel pump under airplane load to load test cell (201) to tested main fuel pump, described oil supply unit (101) is connected with tested main fuel pump, and described oil extraction loads test cell (201) and is connected to form closed-loop path with tested main fuel pump, described oil supply unit (101) comprises fuel tank (1), described fuel tank (1) 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, fuel feeding by-pass throttle valve (21) is provided with 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, described oil extraction is loaded test cell (201) and comprises the back pressure valve (22) connected 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, ball valve (19) is connected with 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 with tested main fuel pump by pipeline, also comprise 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, also comprise 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 first pressure measurement pressure gauge (12), the second pressure measurement pressure gauge (11) are connected with tested main fuel pump respectively with the 3rd pressure measurement pressure gauge (10), 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), described fuel tank (1) is also provided with visual liquid-level meter (24) and liquid level sensor (25), described fuel tank (1) is also provided with 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 |
|---|---|
| CN102996426A CN102996426A (en) | 2013-03-27 |
| CN102996426B true 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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| CN (1) | CN102996426B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109577923A (en) * | 2018-12-03 | 2019-04-05 | 重庆大学 | It is a kind of for measure coal-bed gas exploitation test when reverse irrigation amount device |
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| 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 |
| 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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2012
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109577923A (en) * | 2018-12-03 | 2019-04-05 | 重庆大学 | It is a kind of for measure coal-bed gas exploitation test when reverse irrigation amount device |
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| CN102996426A (en) | 2013-03-27 |
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Granted publication date: 20150826 Termination date: 20191119 |