CN201281012Y - Aviation high-pressure fuel pump test system - Google Patents
Aviation high-pressure fuel pump test system Download PDFInfo
- Publication number
- CN201281012Y CN201281012Y CNU2008201409415U CN200820140941U CN201281012Y CN 201281012 Y CN201281012 Y CN 201281012Y CN U2008201409415 U CNU2008201409415 U CN U2008201409415U CN 200820140941 U CN200820140941 U CN 200820140941U CN 201281012 Y CN201281012 Y CN 201281012Y
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- oil
- fuel pump
- outlet
- test system
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Abstract
The utility model discloses a test system of an aviation high-pressure oil fuel pump, comprising a driving device controlled by an electric control system and an oil supplying system; the test system is characterized in that: the driving device comprises a frequency-conversion motor and a driving interface for arranging an oil fuel pump to be tested, and a shaft joint and a torque gauge are arranged between the frequency-conversion motor and the driving interface; the oil supplying system comprises an oil tank, the outlet of the oil tank is connected to a pressure pump by an oil filter, the outlet of the pressure pump is communicated with an oil inlet pipe, the inlet of the oil tank is communicated with an oil return pipe, and the oil return pipeline passes through a water cooler, the oil inlet pipe and the oil return pipe of the oil supplying system are respectively connected to the inlet and outlet of the oil fuel pump to be tested; the electric control system comprises a control console, a pressure sensor electrically connected to the control console, a flow sensor, a differential pressure sensor and a temperature sensor. The test system can help airline companies to reduce maintaining cost, to shorten maintaining cycle and ensure normal operation of airplanes, therefore, the system plays a promoting roll for the improvement of economic benefit of the airline companies and the reduction of maintaining cost of the airplanes.
Description
Technical field
The utility model relates to a kind of test system of pump, is a kind of aviation high pressure fuel pump test system specifically.
Background technique
The aviation high pressure fuel pump test system that the utility model relates to is developed for newly-increased maintenance items 704300,708300,708600,828300, the 830100 serial Aviation Fuel pump performance tests of newly-increased civil aviation airborne equipment.This series Aviation Fuel pump is that U.S. ARGO-TECH company produces, and is widely used on the BOEING aircraft, with the supporting use of GFM56 series turbofan engine of U.S. GE company production.Along with the continuous development of the civilian transport service of China, the quantity of BOEING aircraft also with day according to increasing, according to market survey, China has this series Aviation Fuel pump and is using surplus surpassing 1000 at present.Because motor is the core component of civil aircraft, and the Aviation Fuel pump is exactly the crucial annex of motor stable operation, and be in high pressure, the work down of big flow status for a long time, so relative failure frequency is higher, because the domestic special test system that does not still have this fuel pump, each airline must deliver to it state's exogenesis producer place under repair and verification, and not only cost of repairs height, and Repair cycle is long.
Summary of the invention
The purpose of this utility model is: provide a kind of can specialty, reliable, aviation high pressure fuel pump test system is finished every testing property of Aviation Fuel pump automatically, has little investment simultaneously, install, characteristics easy to maintenance.
The technical solution of the utility model is:
A kind of aviation high pressure fuel pump test system, comprise drive unit, oil supply system by electric control system controls, it is characterized in that: wherein drive unit comprises variable-frequency motor, and the driving interface of tested fuel pump is installed, and coupling and torsionmeter are installed between the two; Oil supply system comprises fuel tank, the outlet of fuel tank is connected to suction booster through oil purifier, the supercharging delivery side of pump is communicated with oil inlet pipe, the import of fuel tank is communicated with return tube, the pipeline of return tube is by way of water cooler, and the oil inlet pipe of oil supply system and return tube are connected to the import and the outlet of tested fuel pump respectively; Automatical control system comprises operating console and the pressure transducer that is electrically connected with operating console, flow transducer, differential pressure transducer and temperature transducer.
In the Aviation Fuel pump test process, earlier it is installed in and drives on the interface, and connect outside oil circuit, open every switch of oil supply system and (connect oil circuit, cooling line and suction booster), open the control switch of automatical control system again, connect power supply, the suction booster running increases fuel pump import oil pressure, the required rotating speed requirement of input on operating console then, the drive unit running, drive fuel pump to the speed conditions that requires, regulate and test, the rotating speed of fuel pump according to the technical order that relevant maintenance mobile phone requires, output flow and pressure, oil-feed flow and pressure and other parameters all will directly be presented on the instrument of operating console.The working state that the output speed of change drive unit can be regulated fuel pump makes it change the pressure and the flow of output.Can finish test according to relevant service manual to all technical parameters of Aviation Fuel pump.
Aviation high pressure fuel pump Development of Test System success of the present utility model, can test 704300,708300,708600,828300,830100 serial Aviation Fuel pumps, for each airline reduces maintenance expenses, shorten service cycle, guarantee that aircraft normally moves, to improving the economic benefit of airline, reduce the aircraft maintenance cost great promoting effect of will getting up.
Description of drawings
Fig. 1 is the systematic schematic diagram of the utility model aviation high pressure fuel pump test system.
Fig. 2 is the schematic diagram of oil supply system.
Embodiment
Below in conjunction with drawings and Examples the utility model is further specified.
Specific embodiment of the utility model, as shown in Figure 1, a kind of aviation high pressure fuel pump test system, similar to general fuel pump test system, comprise drive unit, oil supply system by electric control system controls, whole system cooperates low-tension distribution box to provide electric power for it by general power, it is characterized in that: wherein drive unit comprises the variable-frequency motor that is equipped with cooling fan, the driving interface of tested fuel pump is installed, coupling and torsionmeter are installed between the two, and automatical control system is controlled the rotating speed of variable-frequency motor by the frequency-variable controller of control variable-frequency motor; Oil supply system comprises fuel tank 1, the outlet of fuel tank 1 is connected to suction booster 2 through oil purifier 6, the outlet of suction booster 2 is communicated with oil inlet pipe 3, the import of fuel tank 1 is communicated with return tube 5, the pipeline of return tube 5 is by way of water cooler 4, the oil inlet pipe 3 of oil supply system and return tube 5 are connected to the import and the outlet of tested fuel pump respectively, as shown in Figure 2; Automatical control system comprises operating console and the pressure transducer that is electrically connected with operating console, flow transducer, differential pressure transducer, temperature transducer and oil purifier 6.Wherein oil purifier 6 is preferably the filter of Y type oil.
Claims (1)
1. aviation high pressure fuel pump test system, comprise drive unit, oil supply system by electric control system controls, it is characterized in that: wherein drive unit comprises variable-frequency motor, and the driving interface of tested fuel pump is installed, and coupling and torsionmeter are installed between the two; Oil supply system comprises fuel tank, the outlet of fuel tank is connected to suction booster through oil purifier, the supercharging delivery side of pump is communicated with oil inlet pipe, the import of fuel tank is communicated with return tube, the pipeline of return tube is by way of water cooler, and the oil inlet pipe of oil supply system and return tube are connected to the import and the outlet of tested fuel pump respectively; Automatical control system comprises operating console and the pressure transducer that is electrically connected with operating console, flow transducer, differential pressure transducer, temperature transducer and oil purifier.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008201409415U CN201281012Y (en) | 2008-10-24 | 2008-10-24 | Aviation high-pressure fuel pump test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008201409415U CN201281012Y (en) | 2008-10-24 | 2008-10-24 | Aviation high-pressure fuel pump test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201281012Y true CN201281012Y (en) | 2009-07-29 |
Family
ID=40927886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008201409415U Expired - Lifetime CN201281012Y (en) | 2008-10-24 | 2008-10-24 | Aviation high-pressure fuel pump test system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201281012Y (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102135090A (en) * | 2011-04-08 | 2011-07-27 | 大庆东达节能技术开发服务有限公司 | Device for detecting efficiency of high-pressure centrifugal water pump on line |
| CN102589860A (en) * | 2012-01-09 | 2012-07-18 | 中国人民解放军海军航空工程学院青岛分院 | Integrated testing system for aviation fuel accessories |
| WO2013086822A1 (en) * | 2011-12-13 | 2013-06-20 | 盛瑞传动股份有限公司 | Automatic gearbox control oil pump test table |
| CN104100512A (en) * | 2013-04-03 | 2014-10-15 | 上海航新航宇机械技术有限公司 | Fuel pump test bed |
| CN108910061A (en) * | 2018-08-07 | 2018-11-30 | 晨龙飞机（荆门）有限公司 | A kind of low dead oil Anti-bubble passenger plane tank mounting of pressure type |
| CN110242553A (en) * | 2019-06-21 | 2019-09-17 | 岭澳核电有限公司 | Nuclear power station oil pumping system test platform and its test method |
| CN114109797A (en) * | 2021-11-05 | 2022-03-01 | 中国航发西安动力控制科技有限公司 | Aviation electric fuel pump test system and method |
| CN115898855A (en) * | 2023-02-10 | 2023-04-04 | 南京航空航天大学金城学院 | Single-double pump test control device and test method |
-
2008
- 2008-10-24 CN CNU2008201409415U patent/CN201281012Y/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102135090A (en) * | 2011-04-08 | 2011-07-27 | 大庆东达节能技术开发服务有限公司 | Device for detecting efficiency of high-pressure centrifugal water pump on line |
| CN102135090B (en) * | 2011-04-08 | 2013-01-02 | 大庆东达节能技术开发服务有限公司 | Device for detecting efficiency of high-pressure centrifugal water pump on line |
| WO2013086822A1 (en) * | 2011-12-13 | 2013-06-20 | 盛瑞传动股份有限公司 | Automatic gearbox control oil pump test table |
| CN102589860A (en) * | 2012-01-09 | 2012-07-18 | 中国人民解放军海军航空工程学院青岛分院 | Integrated testing system for aviation fuel accessories |
| CN102589860B (en) * | 2012-01-09 | 2013-07-10 | 中国人民解放军海军航空工程学院青岛校区 | Integrated testing system for aviation fuel accessories |
| CN104100512A (en) * | 2013-04-03 | 2014-10-15 | 上海航新航宇机械技术有限公司 | Fuel pump test bed |
| CN108910061A (en) * | 2018-08-07 | 2018-11-30 | 晨龙飞机（荆门）有限公司 | A kind of low dead oil Anti-bubble passenger plane tank mounting of pressure type |
| CN110242553A (en) * | 2019-06-21 | 2019-09-17 | 岭澳核电有限公司 | Nuclear power station oil pumping system test platform and its test method |
| CN114109797A (en) * | 2021-11-05 | 2022-03-01 | 中国航发西安动力控制科技有限公司 | Aviation electric fuel pump test system and method |
| CN114109797B (en) * | 2021-11-05 | 2023-10-20 | 中国航发西安动力控制科技有限公司 | Aviation electric fuel pump testing system and method |
| CN115898855A (en) * | 2023-02-10 | 2023-04-04 | 南京航空航天大学金城学院 | Single-double pump test control device and test method |
| CN115898855B (en) * | 2023-02-10 | 2023-12-29 | 南京航空航天大学金城学院 | Single-double pump test control device and test method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20090729 |