CN201548400U - Test system of aviation auxiliary engine fuel regulator - Google Patents
Test system of aviation auxiliary engine fuel regulator Download PDFInfo
- Publication number
- CN201548400U CN201548400U CN2009203135931U CN200920313593U CN201548400U CN 201548400 U CN201548400 U CN 201548400U CN 2009203135931 U CN2009203135931 U CN 2009203135931U CN 200920313593 U CN200920313593 U CN 200920313593U CN 201548400 U CN201548400 U CN 201548400U
- Authority
- CN
- China
- Prior art keywords
- fuel regulator
- oil
- fuel
- detection system
- supply system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Abstract
The utility model discloses a test system of an aviation auxiliary engine fuel regulator. The test system comprises a dragging system, an oil supply system, an air feeding system, and a detecting system, wherein the dragging system comprises a frequency conversion motor, and a coupler is mounted between the frequency conversion motor and a tested fuel regulator; the oil supply system comprises an oil tank and a booster pump, and both an oil inlet pipe and an oil return pipe of the oil supply system are connected with a required pipe orifice of the tested fuel regulator; the air feeding system comprises a nitrogen bottle, and the outlet of the nitrogen bottle is connected with an air pressure adjusting system and a pipeline; and the detecting system comprises a dragging detecting system, a fuel detecting system, and an air feeding detecting system. The test system has the advantages of professionally and reliably finishing all the items of performance testing to the aviation auxiliary engine fuel regulator, reducing maintenance cost, shortening maintenance period, and ensuring normal operation of an airplane, thereby playing a great facilitation of improving economic benefit of an airline and lowering maintenance cost of the airplane.
Description
Technical field
The utility model relates to a kind of test macro, especially relates to a kind of test macro of aviation jack engine fuel regulator.
Background technology
The aviation jack engine is the core component that is only second to the civil aircraft of sustainer, and aviation jack engine fuel regulator is exactly the crucial annex of aviation jack engine steady operation, and often be in the work down of high temperature, high pressure, full load condition, so relative failure frequency is higher, need frequent place under repair and verification.But unprofessional, reliable a complete set of complete test macro in the prior art, so the test of aviation jack engine fuel regulator is very inconvenient.
The utility model content
The utility model has overcome shortcoming of the prior art, a kind of test macro of aviation jack engine fuel regulator is provided, can specialty, finish every performance test reliably to aviation jack engine fuel regulator, have small investment simultaneously, install, characteristics easy to maintenance.
The technical solution of the utility model is: a kind of aviation jack engine fuel regulator test macro, comprise dragging system, oil supply system, air supply system and detection system, described dragging system comprises variable-frequency motor, the driving interface of tested fuel regulator is installed, between variable-frequency motor and tested fuel regulator, shaft coupling is installed; Described oil supply system comprises fuel tank, the outlet of fuel tank is connected to supercharge pump, the supercharging delivery side of pump is communicated with the oil inlet pipe of fuel regulator, and the import of fuel tank is communicated with the scavenge pipe of fuel regulator, and the oil inlet pipe of oil supply system and scavenge pipe are connected to the required mouth of pipe of tested fuel regulator respectively; Described air supply system comprises nitrogen cylinder, and the outlet of nitrogen cylinder is connected to pressure regulation system and pipeline, and the tracheae of air supply system is connected to the required mouth of pipe of tested fuel regulator respectively; Described detection system comprises and drags detection system, fuel oil detection system, air feed detection system.
Described dragging system, oil supply system, air supply system and detection system are by electric control system controls, and described electric-control system comprises control desk, test controller and the pressure that is electrically connected with control desk, differential pressure, flow, angle and temperature sensor.
The outlet of described fuel tank is connected to supercharge pump through oil filter.
In the described fuel tank hydrocooler is arranged.
The outlet of described nitrogen cylinder is connected to pressure regulation system and pipeline through air filter.
Described fuel oil detection system comprises fuel feeding detection system, oil return detection system and oil spout detection system.
Compared with prior art, the utility model has the advantages that: can finish every performance test professional, reliably aviation jack engine fuel regulator, reduce maintenance cost, shorten maintenance cycle, guarantee that aircraft normally moves, to improving the economic benefit of airline, reduce the aircraft maintenance cost and will play great facilitation.
Description of drawings
The utility model will illustrate by example and with reference to the mode of accompanying drawing, wherein:
Fig. 1 is a theory diagram of the present utility model.
Embodiment
Disclosed all features in this instructions, or the step in disclosed all methods or the process except mutually exclusive feature and/or step, all can make up by any way.
Disclosed arbitrary feature in this instructions (comprising any accessory claim, summary and accompanying drawing) is unless special narration all can be replaced by other equivalences or the alternative features with similar purpose.That is, unless special narration, each feature is an example in a series of equivalences or the similar characteristics.
As shown in Figure 1, a kind of aviation jack engine fuel regulator test macro comprises dragging system, oil supply system, air supply system and detection system by electric control system controls.Wherein, dragging system comprises variable-frequency motor 1, and the driving interface of tested fuel regulator 2 is installed, and shaft coupling and rotating speed detector 3 are installed between the two, and the frequency converter 20 of variable-frequency motor connects 380VAC power supply 4; Oil supply system comprises fuel tank 5, the outlet of fuel tank is connected to supercharge pump 6 through oil filter, supercharge pump connects 220VAC power supply 19, the supercharging delivery side of pump is communicated with the oil inlet pipe of tested fuel regulator, be connected with fuel feeding parameter detecting instrument 7 and fuel feeding adjustment control 8 between the oil inlet pipe of supercharge pump and tested fuel regulator, the import of fuel tank is communicated with the scavenge pipe of tested fuel regulator, hydrocooler is arranged in the fuel tank, the oil inlet pipe of oil supply system and scavenge pipe are connected to the required mouth of pipe of tested fuel regulator respectively, be connected with oil return parameter detecting instrument 9 and oil return adjustment controller 10 between the import of fuel tank and the scavenge pipe of tested fuel regulator, tested fuel regulator is connected with oil spout case 14 by pipeline, is connected with oil spout detector 15 and oil spout adjustment control 16 between tested fuel regulator and oil spout case; Air supply system comprises nitrogen cylinder 11, the outlet of nitrogen cylinder is connected to pressure regulation system and pipeline through oil filter, pressure regulation system comprises air feed parameter detecting instrument 12 and source of the gas adjustment control 13, and the tracheae of air supply system is connected to the required mouth of pipe of tested fuel regulator respectively; Electric-control system comprises control desk and test controller 17 and the pressure that is electrically connected with control desk, differential pressure, flow, angle and temperature sensor; Fuel feeding parameter detecting instrument 7, fuel feeding adjustment control 8, oil return parameter detecting instrument 9, oil spout detector 15 and test controller 17 all are connected with 28VDC power supply 18.
In the aviation jack engine fuel regulator test process, earlier fuel regulator is installed on the driving interface, and connects outside supply air line and oil feed line, connect the test control enclosure.Open the every switch of air feed, open every switch (connecting oil circuit, cooling water pipeline and supercharge pump) of oil supply system then, open the gauge tap of electric-control system again, energized, the supercharge pump running increases fuel regulator import oil pressure, the required rotating speed requirement of input on operating console then, the actuator running, drive fuel regulator to the speed conditions that requires, regulate and test according to the technical indicator that relevant servicing manual requires, read and write down the parameters such as rotating speed, delivery rate and pressure, fuel oil temperature and oil spout angle of fuel regulator.The output speed that changes actuator can change the duty of fuel regulator, makes it change the fuel pressure and the flow of output.Can finish test according to relevant servicing manual to all technical parameters of aviation jack engine fuel regulator.
The above only is preferred embodiment of the present utility model; not in order to restriction the utility model; all any modifications of within spirit of the present utility model and principle, being done, be equal to and replace and improvement etc., all should be included within the protection domain of the present utility model.
Claims (6)
1. aviation jack engine fuel regulator test macro, comprise dragging system, oil supply system, air supply system and detection system, it is characterized in that: described dragging system comprises variable-frequency motor, the driving interface of tested fuel regulator is installed, between variable-frequency motor and tested fuel regulator, shaft coupling is installed; Described oil supply system comprises fuel tank, the outlet of fuel tank is connected to supercharge pump, the supercharging delivery side of pump is communicated with the oil inlet pipe of fuel regulator, and the import of fuel tank is communicated with the scavenge pipe of fuel regulator, and the oil inlet pipe of oil supply system and scavenge pipe are connected to the required mouth of pipe of tested fuel regulator respectively; Described air supply system comprises nitrogen cylinder, and the outlet of nitrogen cylinder is connected to pressure regulation system and pipeline, and the tracheae of air supply system is connected to the required mouth of pipe of tested fuel regulator respectively; Described detection system comprises and drags detection system, fuel oil detection system, air feed detection system.
2. aviation jack engine fuel regulator test macro according to claim 1, it is characterized in that: described dragging system, oil supply system, air supply system and detection system are by electric control system controls, and described electric-control system comprises control desk, test controller and the pressure that is electrically connected with control desk, differential pressure, flow, angle and temperature sensor.
3. aviation jack engine fuel regulator test macro according to claim 1 and 2 is characterized in that: the outlet of described fuel tank is connected to supercharge pump through oil filter.
4. aviation jack engine fuel regulator test macro according to claim 1 and 2 is characterized in that: in the described fuel tank hydrocooler is arranged.
5. aviation jack engine fuel regulator test macro according to claim 1 and 2 is characterized in that: the outlet of described nitrogen cylinder is connected to pressure regulation system and pipeline through air filter.
6. aviation jack engine fuel regulator test macro according to claim 1 and 2, it is characterized in that: described fuel oil detection system comprises fuel feeding detection system, oil return detection system and oil spout detection system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203135931U CN201548400U (en) | 2009-10-29 | 2009-10-29 | Test system of aviation auxiliary engine fuel regulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203135931U CN201548400U (en) | 2009-10-29 | 2009-10-29 | Test system of aviation auxiliary engine fuel regulator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201548400U true CN201548400U (en) | 2010-08-11 |
Family
ID=42603575
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009203135931U Expired - Lifetime CN201548400U (en) | 2009-10-29 | 2009-10-29 | Test system of aviation auxiliary engine fuel regulator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201548400U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103384859A (en) * | 2011-02-25 | 2013-11-06 | 斯奈克玛 | Forecasting maintenance operations for an aircraft engine |
| CN103699114A (en) * | 2013-12-13 | 2014-04-02 | 中国燃气涡轮研究院 | Controller and control method for debugging tests of aviation fuel regulating device |
| 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 |
| CN105758646A (en) * | 2016-03-01 | 2016-07-13 | 西安航空动力股份有限公司 | Test device and test method for lubricating oil cut-off of aero-engine afterburner fuel regulator |
| CN105784376A (en) * | 2016-03-01 | 2016-07-20 | 西安航空动力股份有限公司 | Fault eliminating method for performance decay of aero-engine fuel regulator |
| CN107764553A (en) * | 2017-10-23 | 2018-03-06 | 北京理工大学 | A kind of adjustable air inlet heating device pilot system |
| CN109946083A (en) * | 2019-03-29 | 2019-06-28 | 吉林化工学院 | A kind of aero-engine fuel regulator failure diagnosis apparatus |
| CN112747927A (en) * | 2020-12-28 | 2021-05-04 | 中国人民解放军第五七一九工厂 | Test method for detecting high-altitude acceleration oil supply characteristic of main fuel regulator |
-
2009
- 2009-10-29 CN CN2009203135931U patent/CN201548400U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103384859A (en) * | 2011-02-25 | 2013-11-06 | 斯奈克玛 | Forecasting maintenance operations for an aircraft engine |
| CN103699114A (en) * | 2013-12-13 | 2014-04-02 | 中国燃气涡轮研究院 | Controller and control method for debugging tests of aviation fuel regulating device |
| 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 |
| CN105758646A (en) * | 2016-03-01 | 2016-07-13 | 西安航空动力股份有限公司 | Test device and test method for lubricating oil cut-off of aero-engine afterburner fuel regulator |
| CN105784376A (en) * | 2016-03-01 | 2016-07-20 | 西安航空动力股份有限公司 | Fault eliminating method for performance decay of aero-engine fuel regulator |
| CN105784376B (en) * | 2016-03-01 | 2018-06-01 | 西安航空动力股份有限公司 | A kind of troubleshooting method of aero-engine fuel regulator performance degradation |
| CN105758646B (en) * | 2016-03-01 | 2018-08-03 | 西安航空动力股份有限公司 | The disconnected lubricating oil test method of aeroengine thrust augmentation fuel regulator |
| CN107764553A (en) * | 2017-10-23 | 2018-03-06 | 北京理工大学 | A kind of adjustable air inlet heating device pilot system |
| CN109946083A (en) * | 2019-03-29 | 2019-06-28 | 吉林化工学院 | A kind of aero-engine fuel regulator failure diagnosis apparatus |
| CN109946083B (en) * | 2019-03-29 | 2021-03-05 | 吉林化工学院 | Fault diagnosis equipment for fuel regulator of aircraft engine |
| CN112747927A (en) * | 2020-12-28 | 2021-05-04 | 中国人民解放军第五七一九工厂 | Test method for detecting high-altitude acceleration oil supply characteristic of main fuel regulator |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201548400U (en) | Test system of aviation auxiliary engine fuel regulator | |
| CN201281012Y (en) | Aviation high-pressure fuel pump test system | |
| CN101701546B (en) | Sequential turbocharging system anti-surge control device and control method | |
| CN101701874B (en) | Mobile test bed system for test run in external field | |
| CN108005795B (en) | Device and method for controlling angle of inlet guide vane of air compressor in real time | |
| CN101930231B (en) | Test device of fuel controller | |
| CN104931266B (en) | A kind of airplane engine fuel oil analog control system and adjusting method | |
| CN201788411U (en) | Hydraulic test system of fuel controller | |
| CN205559424U (en) | Hydro -cylinder test platform | |
| CN110455547B (en) | High-temperature and high-pressure test system for power machinery combustion chamber test | |
| CN112392756B (en) | Test measurement and control device for electrically-driven centrifugal compressor supercharging system | |
| CN106226060B (en) | Aircraft auxiliary power plant test macro | |
| CN103775326A (en) | Power recovery test-bed for mechanical-compensation type hydraulic pump | |
| CN201788412U (en) | Test device for fuel oil controller | |
| CN105115720A (en) | Test stand used for testing performance of double turbochargers and provided with high-pressure gas shunt device | |
| CN203717315U (en) | Mechanical compensation-type hydraulic pump power recovery testboard | |
| CN205826299U (en) | A kind of EGR valve flow testing system | |
| CN201851209U (en) | Device for preventing surge of turbocharger for marine diesels | |
| CN202451313U (en) | Accessory supercharging system for diesel rack testing | |
| CN101566530B (en) | Test system for electro-hydraulic proportional valve of variable nozzle ring cross-sectional turbocharger | |
| CN202329948U (en) | Test device for simulating working environment to check tightness of workpiece | |
| CN102434333B (en) | Auxiliary pressurization system for diesel engine bench test and using method of auxiliary pressurization system | |
| CN104500381A (en) | Performance testing device for oil pump | |
| CN201583556U (en) | Closed constant flow water supply circulating cooling system with adjustable flow | |
| CN204003790U (en) | Centrifugal governor test stand |
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: 20100811 |