CN101666712A - Tester of aircraft engine lubricating oil pump assembly - Google Patents
Tester of aircraft engine lubricating oil pump assembly Download PDFInfo
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- CN101666712A CN101666712A CN200910187340A CN200910187340A CN101666712A CN 101666712 A CN101666712 A CN 101666712A CN 200910187340 A CN200910187340 A CN 200910187340A CN 200910187340 A CN200910187340 A CN 200910187340A CN 101666712 A CN101666712 A CN 101666712A
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Abstract
The invention provides a tester of an aircraft engine lubricating oil pump assembly, and belongs to the technical field of aircraft engine. The tester comprises a switching valve, a first measuring oil tank, a driving motor, an oil discharging pump, a third-stage oil pump, a pneumatic three-linkage element, a feeding oil pump, a filter, a pressure regulating valve, a first electromagnetic valve, asecond measuring oil tank, a third measuring oil tank, a second electromagnetic valve, an oil filling tank, a one-way valve, an oil filling pump and a cylinder control valve steering device, whereinthe cylinder control valve steering device comprises a first pneumatic control valve, a cylinder and a second pneumatic valve; the tester has the following advantages: a plurality of groups of measuring oil tanks are added for the tester, thus satisfying the requirements of rotating speed, pressure and flow of different specifications; the addition of the oil filling tank ensures that the liquid level of the feeding oil tank is in regulated height range when measuring; the tester improves the test precision of the lubricating oil pump assembly; by using the electromagnetic control cylinder, the tester causes two pneumatic valves to act; and simultaneously, the electromagnetic valve is linked with a time relay, thus ensuring the accuracy of time control when starting and ending the measurement.
Description
Technical field
The invention belongs to the aero engine technology field, particularly a kind of exerciser of aircraft engine oil pump group.
Background technology
Present existing aeromotor exerciser pump adopts a metering oil tank, 8000 rev/mins of maximum speeds, maximum flow is 140 liters/minute, can not satisfy the testing requirements of the high rotating speed of this pump group (9500 rev/mins), big flow (200 liters/minute), need test separately in the period of adjustment of metering oil flow process and oil pump simultaneously, do not satisfy high rotating speed, big flow test field requirement, waste resource simultaneously, efficient is low, working strength is big.
Summary of the invention
Deficiency at the prior art existence; the invention provides a kind of tester of aircraft engine lubricating oil pump assembly; by increasing metering oil tank and Pneumatic valve; with the oil pump group exerciser that is able to satisfy its oil pump group different specification size requirement and satisfies its rotating speed, pressure, traffic requirement, and can play the purpose of safeguard protection effect to hydraulic system.
Technical scheme of the present invention be achieved in that this exerciser comprise switch valve, first metering oil tank, drive motor, the oil pump of draining the oil, 3 grades of oil pumps, pneumatic triple piece, supply oil pump, filtrator, pressure regulator valve, first solenoid valve, second metering oil tank, the 3rd metering oil tank, second solenoid valve, repairing fuel tank, retaining valve, repairing oil pump and cylinder control valve reversing arrangements,, wherein the cylinder control valve reversing arrangement comprises first Pneumatic valve, cylinder and second Pneumatic valve.
The connection of this exerciser is: the outlet of supply tank connects the inlet of 3 grades of oil pumps, 3 grades of oil pumps connect drive motor, the outlet of 3 grades of oil pumps is connection traffic meter and filtrator successively, the outlet of filtrator connects first Pneumatic valve inlet and second Pneumatic valve inlet respectively, the outlet of first Pneumatic valve connects the inlet of first metering oil tank, the outlet of first metering oil tank connects the inlet and second electromagnetic valve entrance of second metering oil tank respectively, the outlet of second metering oil tank connects the 3rd metering oil tank inlet and second electromagnetic valve entrance respectively, second electromagnetic valve outlet connects the oil pump inlet of draining the oil, the oil pump of draining the oil outlet connects the repairing fuel tank inlet, the repairing fuel-tank outlet connects repairing oil pump inlet, the outlet of repairing oil pump connects the supply tank inlet by retaining valve, and the outlet of second pneumatic valve connects the supply tank inlet.
First Pneumatic valve and second Pneumatic valve are same structure in the described cylinder control valve reversing arrangement, comprise valve body, sealing gasket, valve disc, valve rod and threaded connector; Cylinder comprises piston rod, cylinder shell and piston, this connection of installing a side is that sealing gasket is installed on the valve disc, valve disc is connected successively with valve rod, piston rod and piston, wherein sealing gasket, valve disc and valve rod all are positioned at valve body, piston rod and piston are positioned at cylinder shell, and this device opposite side is a symmetrical structure.
Advantage of the present invention is: this exerciser increases many batch totals masuring tank can satisfy different size rotating speed, pressure, traffic requirement, the liquid level of supply tank is at the altitude range of regulation when setting up repairing fuel tank assurance measurement, improve oil pump group measuring accuracy, adopt the solenoid control cylinder that two pneumatic valves are moved, the solenoid valve and the time relay link simultaneously, have guaranteed the accuracy of controlling with the metering end back time when beginning to measure.
Description of drawings
Fig. 1 is a kind of tester of aircraft engine lubricating oil pump assembly structure principle chart of the present invention;
Fig. 2 is a cylinder control valve reversing arrangement structure cut-open view in a kind of tester of aircraft engine lubricating oil pump assembly of the present invention;
1 switch valve among the figure, 2 the 3rd metering oil tanks, 3 second metering oil tanks, 4 first metering oil tanks, 5 drive motor, 6 oil pumps of draining the oil, 73 grades of oil pumps, 8 first Pneumatic valves, 9 cylinders, 10 first solenoid valves, 11 repairing fuel tanks, 12 second Pneumatic valves, 13 pneumatic three connect 14 supply tanks, 15 retaining valves, 16 repairing oil pumps, 17 pressure regulator valves, 18 filtrators, 19 flowmeters, 20 second solenoid valves, 21 tensimeters, 22 valve bodies, 23 sealing gaskets, 24 valve discs, 25 valve rods, 26 threaded connectors, 27 piston rods, 28 cylinder shells, 29 pistons.
Embodiment
A kind of tester of aircraft engine lubricating oil pump assembly detailed structure of the present invention is illustrated with embodiment in conjunction with the accompanying drawings.
Structure of the present invention is: this exerciser comprises switch valve 1, first metering oil tank 4, drive motor 5,6, the 3 grades of oil pumps 7 of oil pump of draining the oil, pneumatic triple piece 13, supply tank 14, filtrator 18, pressure regulator valve 17, first solenoid valve 10, second metering oil tank 3, the 3rd metering oil tank 2, second solenoid valve 20, repairing fuel tank 11, retaining valve 15, repairing oil pump 16 and cylinder control valve reversing arrangement, and wherein the cylinder control valve reversing arrangement comprises first Pneumatic valve 8, cylinder 9 and second Pneumatic valve 12.
The connection of this exerciser is: the outlet of supply tank 14 connects the inlet of 3 grades of oil pumps 7,3 grades of oil pumps 7 connect drive motor 5, the outlet of 3 grades of oil pumps 7 is connection traffic meter 19 and filtrator 18 successively, the outlet of filtrator 18 connects first Pneumatic valve, 8 inlets and second Pneumatic valve, 12 inlets respectively, the outlet of first Pneumatic valve 8 connects the inlet of first metering oil tank 4, the outlet of first metering oil tank 4 connects the inlet and second solenoid valve, 20 inlets of second metering oil tank 3 respectively, 3 outlets of second metering oil tank connect the 3rd metering oil tank 2 inlets and second solenoid valve, 20 inlets respectively, 20 outlets of second solenoid valve connect oil pump 6 inlets of draining the oil, oil pump 6 outlets of draining the oil connect repairing fuel tank 11 inlets, 11 outlets of repairing fuel tank connect repairing oil pump 16 inlets, 16 outlets of repairing oil pump connect supply tank 14 inlets by retaining valve 15, and 12 outlets of second pneumatic valve connect supply tank 14 inlets.
First Pneumatic valve 8 and second Pneumatic valve 12 are same structure in the described cylinder control valve reversing arrangement, comprise valve body 22, sealing gasket 23, valve disc 24, valve rod 25 and threaded connector 26; Cylinder 9 comprises piston rod 27, cylinder shell 28 and piston 29, this connection of installing a side is that sealing gasket 23 is installed on the valve disc 24, valve disc 24 is connected successively with valve rod 25, piston rod 27 and piston 29, wherein sealing gasket 23, valve disc 24 and valve rod 25 all are positioned at valve body 22, piston rod 27 and piston 29 all are positioned at cylinder shell 28, and this device opposite side is a symmetrical structure.
The installation process of this exerciser: 14,3 metering oil tanks of supply tank and Hydraulic Elements all are placed in the operator's console when testing, supply tank 14 is placed on the repairing that is convenient on operator's console right back to 3 metering oil tanks, 3 metering oil tanks are placed on the right side of operator's console, and oil ga(u)ge should show on the instrument panel of control stand.In the instrument panel left side of operator's console 1 Y-150 tensimeter 21 is installed, shows the pressure of oil pump outlet.Correspondence is equipped with 1 pressure meter switch under it; At the pressure regulator valve 17 that the pressure meter switch front end is equipped with, be used for the pressure of fine adjustment oil feed line.1 thermometer is used to show the temperature of metering oil tank.1 electric contact thermometer is used to show and control the temperature of fuel tank.Right-hand part has 1 flow to show control instrument, and the sine wave signal with receiving from turbo flow meter is used for showing the flow that oil pump is total.1 tachometer gage and control knob are used for showing and the control rotating speed of motor.Also have power switch and electromagnetic valve switch, leading on the oil feed line of 3 metering oil tanks has 6 cut-off type two-position two-way solenoid valves, is used to control metering oil tank by every grade of oil pump feed.Drive motor 5 is by a high speed frequency conversion threephase asynchronous; compositions such as two shaft couplings and gear train through walls; driving by the motor of test oil pump is high-speed induction motor; power is 11KW; 2 utmost points; the speed regulation by constant torque scope is 450 rev/mins ~ 12000 rev/mins; satisfy by the requirement of test oil pump; high-speed induction motor adopts inverter supply; the power of frequency converter is 11KW; frequency converter has the defencive function of motor, adopts potentiometer to set rotating speed, and has the motor speed display.Because the medium of this exerciser is a lubricating oil, should be taken into account noise during design, therefore drive motor 5 is placed between isolation, be connected with an end of mechanism through walls by shaft coupling, and the other end of transmission gear train through walls is connected with oil pump by shaft coupling, so just can rotate the drive oil pump by drive motor 5 and carry out work.This device is installed in the rear side of testing table stage body, and the control line of drive motor 5 is received electrical control cashier's office in a shop.Supply tank 14 is by the top that is positioned at 3 metering oil tanks, 3 metering oil tanks are positioned at the control stand viewing position, it is 60～80 ℃ that lubricating oil in supply tank 14 and 3 metering oil tanks all requires temperature, supply tank 14 has heating function, temperature adopts point to connect electropsychrometer and controls automatically, and temperature controlling range is 65～80 ℃.Supply tank 14 has heat-insulation layer, makes fuel tank have heat insulation function.The oil of 3 metering oil tanks is supplied with by supply tank 14, and its oil temperature was guaranteed afterwards by hydraulic system self circulation.
The course of work of this exerciser is: supply tank 14 and repairing fuel tank 11 are injected lubricating oil in the groove scope of testing requirements, close first pneumatic valve 8 and open second pneumatic valve 12, lubricating oil to supply tank 14 and repairing fuel tank 11 heats, when oily temperature reaches the test temperature requirement, lubricating oil is got back to supply tank 14 through filtrator 18, second Pneumatic valve 12, and this process is the running-in test of lubricating oil.After running-in test finishes, drive motor 5 is adjusted the rotating speed that button is adjusted to the test defined by rotating speed, simultaneously with the pressure of pressure regulator valve 17 Adjustment System pressure to defined, press the button of first solenoid valve 10, make cylinder 9 commutations, at this moment first Pneumatic valve 8 is connected, second Pneumatic valve 12 disconnects simultaneously, lubricating oil flows into first metering oil tank 4 through first Pneumatic valve 8, begins to measure, and the time relay in first solenoid valve 10 picks up counting simultaneously.In metering process, to observe the oil level of supply tank 14 at any time, when oil level is lower than the groove of requirement oil level, start repairing oil pump 16, lubricating oil carries out repairing from repairing fuel tank 11 to supply tank 14, when supply tank 14 oil levels are higher than the groove of oil level, stop repairing oil pump 16.After reaching setting-up time, 10 automatic cutouts of first solenoid valve, cylinder 9 commutations, at this moment second Pneumatic valve 12 is connected, first Pneumatic valve 8 disconnects simultaneously, at this moment the flow that shows of first metering oil tank 14, second metering oil tank 3 and the 3rd metering oil tank 2 is the flow when regulation rotating speed and pressure.Metering finishes, and connects second solenoid valve 20, starts oil pump 6 lubricating oil of draining the oil and flows into supply tank 14 from first metering oil tank 4, second metering oil tank 3 and the 3rd metering oil tank 2, and whole test process finishes.
Wherein the course of work of cylinder control valve reversing arrangement is as follows: during oil pump work, 10 outages of first solenoid valve, pressurized air enters the left chamber of cylinder 9, and this moment, piston rod 27 moved right, first Pneumatic valve 8 is in open mode, and second Pneumatic valve 12 is in closed condition; This moment, lubricating oil directly flowed back to supply tank 14 through first Pneumatic valve 8.When carrying out flow metering, 10 energisings of first solenoid valve, pressurized air enters the right chamber of cylinder 9, promoting piston rod 27 is moved to the left, second Pneumatic valve 12 is in open mode, and first Pneumatic valve 8 is in closed condition, and lubricating oil flows directly into first metering oil tank 4 through second Pneumatic valve 12; When connecting first solenoid valve 10, the time relay work that picks up counting, first solenoid valve 10 cuts off the power supply automatically after finishing time of setting, and the lubricating oil that flows into first metering oil tank 4, second metering oil tank 3 and the 3rd metering oil tank 2 this moment is the average discharge in the unit interval.
Claims (2)
1, a kind of tester of aircraft engine lubricating oil pump assembly, this exerciser is by switch valve (1), first metering oil tank (4), drive motor (5), the oil pump (6) of draining the oil, 3 grades of oil pumps (7), pneumatic triple piece (13), supply tank (14), filtrator (18) and pressure regulator valve (17) are formed, it is characterized in that: this exerciser also comprises first solenoid valve (10), second metering oil tank (3), the 3rd metering oil tank (2), second solenoid valve (20), repairing fuel tank (11), retaining valve (15), repairing oil pump (16) and cylinder control valve reversing arrangement, wherein the cylinder control valve reversing arrangement comprises first Pneumatic valve (8), cylinder (9) and second Pneumatic valve (12); The connection of this exerciser is: the outlet of supply tank (14) connects the inlet of 3 grades of oil pumps (7), 3 grades of oil pumps (7) connect drive motor (5), the outlet of 3 grades of oil pumps (7) is connection traffic meter (19) and filtrator (18) successively, the outlet of filtrator (18) connects first Pneumatic valve (8) inlet and second Pneumatic valve (12) inlet respectively, the outlet of first Pneumatic valve (8) connects the inlet of first metering oil tank (4), the outlet of first metering oil tank (4) connects the inlet and second solenoid valve (20) inlet of second metering oil tank (3) respectively, second metering oil tank (3) outlet connects the 3rd metering oil tank (2) inlet and second solenoid valve (20) inlet respectively, second solenoid valve (20) outlet connects oil pump (6) inlet of draining the oil, the oil pump (6) of draining the oil outlet connects repairing fuel tank (11) inlet, repairing fuel tank (11) outlet connects repairing oil pump (16) inlet, repairing oil pump (16) outlet connects supply tank (14) inlet by retaining valve (15), and second pneumatic valve (12) outlet connects supply tank (14) inlet.
2, by the described tester of aircraft engine lubricating oil pump assembly of claim 1, it is characterized in that first Pneumatic valve (8) and second Pneumatic valve (12) are same structure in the described cylinder control valve reversing arrangement, comprise valve body (22), sealing gasket (23), valve disc (24), valve rod (25) and threaded connector (26); Cylinder (9) comprises piston rod (27), cylinder shell (28) and piston (29), this connection of installing a side is that sealing gasket (23) is installed on the valve disc (24), valve disc (24) is connected successively with valve rod (25), piston rod (27) and piston (29), wherein sealing gasket (23), valve disc (24) and valve rod (25) all are positioned at valve body (22), piston rod (27) and piston (29) all are positioned at cylinder shell (28), and this device opposite side is a symmetrical structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101873409A CN101666712B (en) | 2009-09-14 | 2009-09-14 | Tester of aircraft engine lubricating oil pump assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101873409A CN101666712B (en) | 2009-09-14 | 2009-09-14 | Tester of aircraft engine lubricating oil pump assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101666712A true CN101666712A (en) | 2010-03-10 |
| CN101666712B CN101666712B (en) | 2011-01-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2009101873409A Expired - Fee Related CN101666712B (en) | 2009-09-14 | 2009-09-14 | Tester of aircraft engine lubricating oil pump assembly |
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Cited By (13)
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| CN101832800A (en) * | 2010-05-20 | 2010-09-15 | 郑州共赢铁路设备有限公司 | Liquid turbine-based fuel metering device |
| CN101930231A (en) * | 2010-08-27 | 2010-12-29 | 武汉航达航空科技发展有限公司 | Test device of fuel controller |
| CN102353542A (en) * | 2011-09-28 | 2012-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Lubricant pump testing device for automatically measuring flow of aeroengine and control method thereof |
| 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 |
| CN102954872A (en) * | 2012-10-12 | 2013-03-06 | 湖北航达科技有限公司 | High-temperature fuel test bed for aircraft hydraulic element |
| CN103045822A (en) * | 2012-12-19 | 2013-04-17 | 苏州工业园区姑苏科技有限公司 | Automatic oil supplementing control device of oil groove |
| CN103279143A (en) * | 2013-05-10 | 2013-09-04 | 西安航空动力股份有限公司 | Oil supply system for test device of lubricating oil pump unit of gas turbine |
| CN103604565A (en) * | 2013-11-26 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Hydraulic seal and hydraulic movement testing device for aero-engine assembly field |
| CN105510037A (en) * | 2015-12-03 | 2016-04-20 | 中国航空动力机械研究所 | High altitude test system and method for aircraft engine oil system |
| CN105571870A (en) * | 2016-01-13 | 2016-05-11 | 中国航空动力机械研究所 | Whole engine slide oil interruption test apparatus for turboshaft engine |
| CN106124219A (en) * | 2016-05-31 | 2016-11-16 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of assay device verifying oil pump function of having no progeny in lubricating oil and verification method |
| CN110905754A (en) * | 2019-09-02 | 2020-03-24 | 苏州悦奇宁流体自动化科技有限公司 | High-precision flow control system |
| CN115371979A (en) * | 2022-10-24 | 2022-11-22 | 四川新川航空仪器有限责任公司 | Three-phase eddy current separator performance evaluation test equipment |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101832800B (en) * | 2010-05-20 | 2011-11-16 | 郑州共赢铁路设备有限公司 | Liquid turbine-based fuel metering device |
| CN101832800A (en) * | 2010-05-20 | 2010-09-15 | 郑州共赢铁路设备有限公司 | Liquid turbine-based fuel metering device |
| CN101930231A (en) * | 2010-08-27 | 2010-12-29 | 武汉航达航空科技发展有限公司 | Test device of fuel controller |
| CN102353542A (en) * | 2011-09-28 | 2012-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Lubricant pump testing device for automatically measuring flow of aeroengine and control method thereof |
| CN102353542B (en) * | 2011-09-28 | 2014-05-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Lubricant pump testing device for automatically measuring flow of aeroengine and control method thereof |
| 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 |
| 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 |
| CN102954872A (en) * | 2012-10-12 | 2013-03-06 | 湖北航达科技有限公司 | High-temperature fuel test bed for aircraft hydraulic element |
| CN103045822A (en) * | 2012-12-19 | 2013-04-17 | 苏州工业园区姑苏科技有限公司 | Automatic oil supplementing control device of oil groove |
| CN103279143B (en) * | 2013-05-10 | 2015-07-01 | 西安航空动力股份有限公司 | Oil supply system for test device of lubricating oil pump unit of gas turbine |
| CN103279143A (en) * | 2013-05-10 | 2013-09-04 | 西安航空动力股份有限公司 | Oil supply system for test device of lubricating oil pump unit of gas turbine |
| CN103604565A (en) * | 2013-11-26 | 2014-02-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Hydraulic seal and hydraulic movement testing device for aero-engine assembly field |
| CN103604565B (en) * | 2013-11-26 | 2016-01-20 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aeromotor erecting yard hydraulic seal and hydraulic operation test unit |
| CN105510037B (en) * | 2015-12-03 | 2018-03-30 | 中国航空动力机械研究所 | A kind of altitude pilot system of Aero-Engine Lubrication System and method |
| CN105510037A (en) * | 2015-12-03 | 2016-04-20 | 中国航空动力机械研究所 | High altitude test system and method for aircraft engine oil system |
| CN105571870A (en) * | 2016-01-13 | 2016-05-11 | 中国航空动力机械研究所 | Whole engine slide oil interruption test apparatus for turboshaft engine |
| CN105571870B (en) * | 2016-01-13 | 2018-12-04 | 中国航空动力机械研究所 | Turboshaft engine complete machine lubricating oil abort device |
| CN106124219A (en) * | 2016-05-31 | 2016-11-16 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of assay device verifying oil pump function of having no progeny in lubricating oil and verification method |
| CN106124219B (en) * | 2016-05-31 | 2018-12-11 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of experimental rig and verification method for verifying lubricating oil pumping function after lubricating oil interrupts |
| CN110905754A (en) * | 2019-09-02 | 2020-03-24 | 苏州悦奇宁流体自动化科技有限公司 | High-precision flow control system |
| CN115371979A (en) * | 2022-10-24 | 2022-11-22 | 四川新川航空仪器有限责任公司 | Three-phase eddy current separator performance evaluation test equipment |
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| CN101666712B (en) | 2011-01-19 |
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