CN203584929U - Aero-engine test bay hydraulic pump load system - Google Patents
Aero-engine test bay hydraulic pump load system Download PDFInfo
- Publication number
- CN203584929U CN203584929U CN201320687885.8U CN201320687885U CN203584929U CN 203584929 U CN203584929 U CN 203584929U CN 201320687885 U CN201320687885 U CN 201320687885U CN 203584929 U CN203584929 U CN 203584929U
- Authority
- CN
- China
- Prior art keywords
- hydraulic pump
- oil hydraulic
- oil
- flow
- load 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 - Fee Related
Links
Images
Abstract
An aero-engine test bay hydraulic pump load system comprises an oil supply assembly, an oil supply pipeline, a hydraulic pump, a high-pressure pipeline, nine adjustable throttling nozzles, a hydraulic control valve, a solenoid valve, a flow meter and an oil returning pipeline. A set flow control assembly is composed of the adjustable throttling nozzles, the hydraulic control valve and the solenoid valve. The oil supply assembly is connected with the inlet of the hydraulic pump through the oil supply pipeline, an engine drives the hydraulic pump, the hydraulic pump is connected with the set flow control assembly through the high-pressure pipeline, and the flow meter is installed on the oil returning pipeline. The front 6-7 throttling nozzles are used for carrying out flow distribution according to the load spectrum flow of the engine, and the remaining 2-3 throttling nozzles are small-flow fine adjusting throttling nozzles. The aero-engine test bay hydraulic pump load system has the advantages of being small in floor space, flexible in change, low in failure rate, high in responding speed and accurate in flow control.
Description
Technical field
The present invention relates to aeroengine ground run field, particularly a kind of aircraft engine test stand oil hydraulic pump load system.
Background technique
One of predominant use of aeroengine machine driven system is for the aviation accessory runnings such as the oil hydraulic pump of aircraft provide power, and mechanical work is transformed into hydraulic pressure kinetic energy, and the various hydraulic systems earthward and under regime of flight provide hydraulic power.In each model engine production certification test, transmission system need to complete the running-in test of full load state, the functional check before dispatching from the factory, and wherein oil hydraulic pump is the basic load of transmission system load.
Because Test-bed cannot be installed complicated plane hydraulic system, the general simulation load system that uses consumes the hydraulic energy that oil hydraulic pump produces.So the oil hydraulic pump load system of test bay need to, according to the loading spectrum of tested engine test, strictly be controlled the rate of discharge of oil hydraulic pump.Tradition aircraft engine test stand because of model single, test bay simulation load system be all special device, function singleness, after rigging up and debugging is qualified, parameter adjustment is quite difficult.Along with the research and development of aeroengine, test bay, to polytypic future development, requires simulation load system to have stronger universal performance, can be flexible and changeable.
Summary of the invention
The object of the invention is in order to solve the problem that original device performance is single, spy provides a kind of aircraft engine test stand oil hydraulic pump load system.
The invention provides a kind of aircraft engine test stand oil hydraulic pump load system, it is characterized in that: described aircraft engine test stand oil hydraulic pump load system, comprises fuel feeding assembly 1, oil feed line 2, oil hydraulic pump 3, pressure duct 4, adjustable stem bar 5, hydraulic control valve 6, solenoid valve 7, flowmeter 8, return line 9;
Wherein: adjustable stem bar 5, hydraulic control valve 6 and the common composition group flow control assembly of solenoid valve 7; Fuel feeding assembly 1 is connected with the import of oil hydraulic pump 3 by oil feed line 2, driven by engine oil hydraulic pump 3, and oil hydraulic pump 3 is connected with group flow control assembly by pressure duct 4, and flowmeter 8 is arranged on return line 9.
Hydraulic oil arrives the import of oil hydraulic pump 3, driven by engine oil hydraulic pump rotation acting, the pressure of raising hydraulic oil through oil feed line 2 from fuel feeding assembly 1; High pressure liquid force feed is by pressure duct 4 arrival group flow control assemblies.Flow control assembly is converted into kinetic energy by the pressure potential of hydraulic oil, the input work of consumption of engine; Final hydraulic oil is got back to engine intake, periodic duty by flowmeter and return line 9.
The number of described adjustable stem bar 5 is 9.
When keeping constant oil hydraulic pump outlet pressure, input power P
iq is directly proportional to oil hydraulic pump flow, so the oil hydraulic pump load system of test bay need to, according to the loading spectrum of tested engine test, strictly be controlled the rate of discharge of oil hydraulic pump;
According to formula
the working principle of constant pressure variable displacement pump, the input power P of oil hydraulic pump
iq is directly proportional to oil hydraulic pump flow.Test bay control centre, by programmable controller, connects the solenoid valve 7 of one or more flow control assemblies, opens the hydraulic control valve 6 of adjustable stem bar 5 belows, makes high pressure liquid force feed through adjustable stem bar 5 step-downs, consumes the power of oil hydraulic pump.The number of adjustable stem bar 5 is 9, wherein front 6～7 flow nipples carry out assignment of traffic according to the loading spectrum flow of motor, remaining 2～3 flow nipples is small flow fine adjustment stem bar, during actual use, according to loading spectrum, open at the appointed time the stream of one or more flow nipples simultaneously, when flow has deviation, by fine adjustment stem bar, supplement;
Wherein: P
i-input power p-oil hydraulic pump outlet pressure
Q-oil hydraulic pump flow η-oil hydraulic pump efficiency.
Advantage of the present invention:
Aircraft engine test stand oil hydraulic pump load system of the present invention, floor space is little, variation is flexible, failure rate is low, speed of response is high, and flow control is accurate.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is aircraft engine test stand oil hydraulic pump load system theory structure schematic diagram.
Embodiment
Embodiment 1
The present embodiment provides a kind of aircraft engine test stand oil hydraulic pump load system, it is characterized in that: described aircraft engine test stand oil hydraulic pump load system, comprises fuel feeding assembly 1, oil feed line 2, oil hydraulic pump 3, pressure duct 4, adjustable stem bar 5, hydraulic control valve 6, solenoid valve 7, flowmeter 8, return line 9;
Wherein: adjustable stem bar 5, hydraulic control valve 6 and the common composition group flow control assembly of solenoid valve 7; Fuel feeding assembly 1 is connected with the import of oil hydraulic pump 3 by oil feed line 2, driven by engine oil hydraulic pump 3, and oil hydraulic pump 3 is connected with group flow control assembly by pressure duct 4, and flowmeter 8 is arranged on return line 9.
Hydraulic oil arrives the import of oil hydraulic pump 3, driven by engine oil hydraulic pump rotation acting, the pressure of raising hydraulic oil through oil feed line 2 from fuel feeding assembly 1; High pressure liquid force feed is by pressure duct 4 arrival group flow control assemblies.Flow control assembly is converted into kinetic energy by the pressure potential of hydraulic oil, the input work of consumption of engine; Final hydraulic oil is got back to engine intake, periodic duty by flowmeter and return line 9.
The number of described adjustable stem bar 5 is 9.
When keeping constant oil hydraulic pump outlet pressure, input power P
iq is directly proportional to oil hydraulic pump flow, so the oil hydraulic pump load system of test bay need to, according to the loading spectrum of tested engine test, strictly be controlled the rate of discharge of oil hydraulic pump;
According to formula
the working principle of constant pressure variable displacement pump, the input power P of oil hydraulic pump
iq is directly proportional to oil hydraulic pump flow.Test bay control centre, by programmable controller, connects the solenoid valve 7 of one or more flow control assemblies, opens the hydraulic control valve 6 of adjustable stem bar 5 belows, makes high pressure liquid force feed through adjustable stem bar 5 step-downs, consumes the power of oil hydraulic pump.The number of adjustable stem bar 5 is 9, wherein front 6 flow nipples carry out assignment of traffic according to the loading spectrum flow of motor, remaining 3 flow nipples is small flow fine adjustment stem bar, during actual use, according to loading spectrum, open at the appointed time the stream of one or more flow nipples simultaneously, when flow has deviation, by fine adjustment stem bar, supplement;
Wherein: P
i-input power p-oil hydraulic pump outlet pressure
Q-oil hydraulic pump flow η-oil hydraulic pump efficiency.
Embodiment 2
The present embodiment provides a kind of aircraft engine test stand oil hydraulic pump load system, it is characterized in that: described aircraft engine test stand oil hydraulic pump load system, comprises fuel feeding assembly 1, oil feed line 2, oil hydraulic pump 3, pressure duct 4, adjustable stem bar 5, hydraulic control valve 6, solenoid valve 7, flowmeter 8, return line 9;
Wherein: adjustable stem bar 5, hydraulic control valve 6 and the common composition group flow control assembly of solenoid valve 7; Fuel feeding assembly 1 is connected with the import of oil hydraulic pump 3 by oil feed line 2, driven by engine oil hydraulic pump 3, and oil hydraulic pump 3 is connected with group flow control assembly by pressure duct 4, and flowmeter 8 is arranged on return line 9.
Hydraulic oil arrives the import of oil hydraulic pump 3, driven by engine oil hydraulic pump rotation acting, the pressure of raising hydraulic oil through oil feed line 2 from fuel feeding assembly 1; High pressure liquid force feed is by pressure duct 4 arrival group flow control assemblies.Flow control assembly is converted into kinetic energy by the pressure potential of hydraulic oil, the input work of consumption of engine; Final hydraulic oil is got back to engine intake, periodic duty by flowmeter and return line 9.
The number of described adjustable stem bar 5 is 9.
When keeping constant oil hydraulic pump outlet pressure, input power P
iq is directly proportional to oil hydraulic pump flow, so the oil hydraulic pump load system of test bay need to, according to the loading spectrum of tested engine test, strictly be controlled the rate of discharge of oil hydraulic pump;
According to formula
the working principle of constant pressure variable displacement pump, the input power P of oil hydraulic pump
iq is directly proportional to oil hydraulic pump flow.Test bay control centre, by programmable controller, connects the solenoid valve 7 of one or more flow control assemblies, opens the hydraulic control valve 6 of adjustable stem bar 5 belows, makes high pressure liquid force feed through adjustable stem bar 5 step-downs, consumes the power of oil hydraulic pump.The number of adjustable stem bar 5 is 9, wherein front 7 flow nipples carry out assignment of traffic according to the loading spectrum flow of motor, remaining 2 flow nipples is small flow fine adjustment stem bar, during actual use, according to loading spectrum, open at the appointed time the stream of one or more flow nipples simultaneously, when flow has deviation, by fine adjustment stem bar, supplement;
Wherein: P
i-input power p-oil hydraulic pump outlet pressure
Q-oil hydraulic pump flow η-oil hydraulic pump efficiency.
Claims (2)
1. an aircraft engine test stand oil hydraulic pump load system, it is characterized in that: described aircraft engine test stand oil hydraulic pump load system, comprises fuel feeding assembly (1), oil feed line (2), oil hydraulic pump (3), pressure duct (4), adjustable stem bar (5), hydraulic control valve (6), solenoid valve (7), flowmeter (8), return line (9);
Wherein: the common composition group flow control assembly of adjustable stem bar (5), hydraulic control valve (6) and solenoid valve (7); Fuel feeding assembly (1) is connected with the import of oil hydraulic pump (3) by oil feed line (2), driven by engine oil hydraulic pump (3), and oil hydraulic pump (3) is connected with group flow control assembly by pressure duct (4), and flowmeter (8) is arranged on return line (9).
2. according to aircraft engine test stand oil hydraulic pump load system claimed in claim 1, it is characterized in that: the number of described adjustable stem bar (5) is 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320687885.8U CN203584929U (en) | 2013-11-04 | 2013-11-04 | Aero-engine test bay hydraulic pump load system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320687885.8U CN203584929U (en) | 2013-11-04 | 2013-11-04 | Aero-engine test bay hydraulic pump load system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203584929U true CN203584929U (en) | 2014-05-07 |
Family
ID=50582859
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320687885.8U Expired - Fee Related CN203584929U (en) | 2013-11-04 | 2013-11-04 | Aero-engine test bay hydraulic pump load system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203584929U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575539A (en) * | 2013-11-04 | 2014-02-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Hydraulic pump load system of test bed for aircraft engine and flow control method |
| CN104454690A (en) * | 2014-12-03 | 2015-03-25 | 成都发动机（集团）有限公司 | Hydraulic pump loading system for simultaneously performing ground test on two types of aero-engines |
| CN106593968A (en) * | 2016-12-14 | 2017-04-26 | 成都发动机（集团）有限公司 | Hydraulic pump load control system for one-engine double-pump aero-engine ground test |
-
2013
- 2013-11-04 CN CN201320687885.8U patent/CN203584929U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575539A (en) * | 2013-11-04 | 2014-02-12 | 沈阳黎明航空发动机(集团)有限责任公司 | Hydraulic pump load system of test bed for aircraft engine and flow control method |
| CN104454690A (en) * | 2014-12-03 | 2015-03-25 | 成都发动机（集团）有限公司 | Hydraulic pump loading system for simultaneously performing ground test on two types of aero-engines |
| CN106593968A (en) * | 2016-12-14 | 2017-04-26 | 成都发动机（集团）有限公司 | Hydraulic pump load control system for one-engine double-pump aero-engine ground test |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8666632B2 (en) | Distributed aircraft engine fuel system | |
| CN104481704B (en) | One realizes fuel real-time control method and device in Study On Start-up Process For Gas Turbines | |
| CN203584929U (en) | Aero-engine test bay hydraulic pump load system | |
| ATE405736T1 (en) | FUEL SYSTEM WITH DEMAND MEASUREMENT FOR GAS TURBINES | |
| EP2500551A3 (en) | Fuel flow control system and method for controlling two positive displacement pumps | |
| CN103575539A (en) | Hydraulic pump load system of test bed for aircraft engine and flow control method | |
| US8499542B2 (en) | Flow balancing valve | |
| CN101438039B (en) | Modular fuel supply device for a gas turbine | |
| CN103630314A (en) | Blade high on-line air flow excitation system and test method | |
| RU2507406C1 (en) | Fuel feed system for gas turbine engine with augmenter | |
| CN102673794A (en) | Overhead fuel drainage device using fuel supply pumps as power | |
| CN101788396B (en) | Performance testing system of pressure-superposed water supply equipment | |
| CN103423218A (en) | Load-sensitive valve control integrated load loading device and control method thereof | |
| CN201788412U (en) | Test device for fuel oil controller | |
| CN203587313U (en) | Vacuum-pumping device system of wind tunnel pumping experiment | |
| CN204677522U (en) | A kind of confession pressing system of fluid motor-driven oil sources | |
| CN203894056U (en) | Tester comprehensive stepless oil supply apparatus | |
| CN203114798U (en) | Energy-saving servo hydraulic station | |
| RU2622683C1 (en) | Gas-turbine engine fuel supply system | |
| CN102707739B (en) | Working state control system and control method for pumping oil supply simulation chamber | |
| CN105181337A (en) | Test bed engine oil supply system and application method thereof | |
| CN103527564A (en) | Method for adjusting return oil pressure of hydraulic pump shell | |
| CN212229443U (en) | Full-real information source semi-physical simulation system of aircraft engine | |
| CN204283626U (en) | Fuel closed-loop control device in a kind of Study On Start-up Process For Gas Turbines | |
| CN203708161U (en) | Load-sensitive control system of high-precision hydraulic generator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140507 Termination date: 20171104 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |