CN104454690B - Can be used for the hydraulic pump load system of two kinds of type aero-engines ground run simultaneously - Google Patents
Can be used for the hydraulic pump load system of two kinds of type aero-engines ground run simultaneously Download PDFInfo
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- CN104454690B CN104454690B CN201410728490.7A CN201410728490A CN104454690B CN 104454690 B CN104454690 B CN 104454690B CN 201410728490 A CN201410728490 A CN 201410728490A CN 104454690 B CN104454690 B CN 104454690B
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- hydraulic pump
- oil
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- engine
- pump load
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B11/00—Servomotor systems without provision for follow-up action; Circuits therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B13/00—Details of servomotor systems ; Valves for servomotor systems
- F15B13/02—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
- F15B13/06—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with two or more servomotors
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supply Devices, Intensifiers, Converters, And Telemotors (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
Can be used for the hydraulic pump load system of two kinds of type aero-engines ground run simultaneously, including hydraulic pump load station, the flowline of hydraulic pump load station is connected in parallel promising first engine hydraulic pump the first in-line of pressure oil is provided and the second in-line of pressure oil is provided for the second engine hydraulic pump, the return line of hydraulic pump load station is provided with flow control valve；During test run, the oil-in of the first engine hydraulic pump, the oil-in of the second engine hydraulic pump are connected with described first in-line, the second in-line respectively, the oil-out of the first engine hydraulic pump, the oil-out of the second engine hydraulic pump are connected with the return line of hydraulic pump load station by snap joint and pipe fitting respectively, and before being connected to flow control valve.
Description
Technical field
The invention belongs to aero-engine ground run technical field, the hydraulic pump particularly to aero-engine ground run loads
System.
Background technology
Domestic existing aircraft engine test stand frame, is all that a kind of model electromotor uses a set of its Test Rig, in process equipment side
Face, is also that a kind of model electromotor uses a set of hydraulic pump load system, and two electromotors can not be carried out test run simultaneously.Cause
And there is problems in that 1, the electromotor of every kind of model must have corresponding hydraulic pump load system, thus hydraulic pump load system
Quantity be continuously increased, the fund of consuming and land resource increase, and the production cost of electromotor improves.2, can not be simultaneously to two
Electromotor carries out test run, affects test run efficiency.
Summary of the invention
It is an object of the invention to overcome the deficiencies in the prior art, it is provided that one can be used for two kinds of type aero-engines ground simultaneously
The hydraulic pump load system of test run, to economize on resources, reduces cost, improves test run efficiency.
The hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention, bears including hydraulic pump
Carry station, the flowline of hydraulic pump load station is connected in parallel promising first engine hydraulic pump the first oil inlet pipe of pressure oil is provided
Road and the second in-line for the second engine hydraulic pump offer pressure oil, be provided with on the return line of hydraulic pump load station
Flow control valve；During test run, the oil-in of the first engine hydraulic pump, the second engine hydraulic pump oil-in respectively with described
First in-line, second in-line connect, the oil-out of the first engine hydraulic pump, the second engine hydraulic pump fuel-displaced
Mouth is connected with the return line of hydraulic pump load station by snap joint and pipe fitting respectively, and before being connected to flow control valve.
The hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention, its hydraulic pump loads
The pressure oil tank stood is provided with leak oil line joint, during test run, if engine hydraulic pump needs leakage of oil, then and can be by engine hydraulic pump
The leak oil line joint that arranged with pressure oil tank by pipe fitting of oil leakaging port be connected, if engine hydraulic pump need not leakage of oil, then can be by
The leak oil line joint that pressure oil tank is arranged cuts out.
The hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention, its first oil inlet pipe
Road is identical with the structure of the second in-line, is passed through pipe fitting by the first oil strainer, the second oil strainer and oil-feed control valve successively
It is connected in series composition.
The method have the advantages that
1, on flowline, the first oil inlet pipe it is connected in parallel to due to the hydraulic pump load station in hydraulic pump load system of the present invention
Road and the second in-line, be provided with flow control valve on return line, it is thus achieved that a set of hydraulic pump load system can supply
The electromotor of two kinds of types carries out ground run, and two electromotors can be carried out test run simultaneously.
2, ground run can be carried out for the electromotor of two kinds of types due to a set of hydraulic pump load system, and can be simultaneously to two electromotors
Carry out test run, thus not only can economize on resources, reduce cost, and test run efficiency can be improved.
3, with hydraulic pump load system of the present invention, aero-engine being carried out ground run, stability of flow, controlling is good, complete
Test run quality all can be ensured.
Accompanying drawing explanation
Fig. 1 is the first of the hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention
Structured flowchart；
Fig. 2 is the second of the hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention
Structured flowchart；
Fig. 3 is the third of the hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention
Structured flowchart；
Fig. 4 is the first of the hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention
Hydraulic schematic diagram；
Fig. 5 is the second of the hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention
Hydraulic schematic diagram；
Fig. 6 is the third of the hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention
Hydraulic schematic diagram.
In figure, 1-gas cylinder, 2-air relief valve, 3-air filter, 4-needle valve, 5-gas exhausting valve (bite type ball valve),
6-relief valve, 7-funnel, 8-refueling control valve (ball valve), 9-pressure oil tank, 10-goes out oil control valve (ball valve), and 11
-heat exchanger, 12-water supply control valve (electromagnetic valve), 13-liquidometer, 14-overflow valve, 15-leading hydraulic control one-way valve,
16-soft handover wet solenoid valve, 17-oil return control valve (ball valve), 18-choke valve, 19-first-class gauge (turbine flow
Meter), 20 second gauge (turbine flowmeter), 21-pressure meter switch, 22-Pressure gauge, 23-the first oil strainer, 24
-the second oil strainer, 25-oil-feed control valve (ball valve), 26-snap joint, 27-the 3rd oil strainer, 28-accumulator,
29-water-returning control valve (ball valve), 30-leak oil line joint, 31-blowdown control valve, b1-hydraulic pump load station, b2-first
Engine hydraulic pump, b3-the second engine hydraulic pump.
Detailed description of the invention
Below by embodiment and combine accompanying drawing to the liquid that can be used for the ground run simultaneously of two kinds of type aero-engines of the present invention
Press pump load system is described further.
Embodiment 1
In the present embodiment, can be used for structured flowchart such as Fig. 1 of the hydraulic pump load system of two kinds of type aero-engine ground runs
Shown in, hydraulic schematic diagram as shown in Figure 4, including hydraulic pump load station b1, is connected in parallel on the flowline of hydraulic pump load station
Promising first engine hydraulic pump provides the first in-line of pressure oil and provides the second of pressure oil for the second engine hydraulic pump
In-line, is provided with flow control valve on the return line of hydraulic pump load station.
From fig. 4, it can be seen that hydraulic pump load station b1 includes pressure oil tank 9, pressure oil tank 9 connects gas cylinder 1, air relief valve
What 2, air filter 3, needle valve 4 formed adds pressure gas channel, and gas exhausting valve (bite type ball valve) 5, relief valve 6 form
Gas exhaust piping, funnel 7, refueling control valve (ball valve) 8 composition filling conduit, pipe fitting and blowdown control valve (ball valve) 31
Drain the oil blowoff line and the leak oil line joint 30 of composition；First in-line in parallel on the flowline of hydraulic pump load station b1,
Second oil inlet pipeline structure is identical, successively by the first oil strainer the 23, second oil strainer 24 and oil-feed control valve (ball valve)
25 are connected in series composition by pipe fitting；The flow control valve arranged on the return line of hydraulic pump load station b1 is by three groups of parallel connections even
Connecing composition, often group flow control valve is formed by leading hydraulic control one-way valve 15, soft handover wet solenoid valve and choke valve 18,
After flow control valve, it is additionally provided with overflow valve 14, the oil return pipe in parallel with flow control valve is additionally provided with oil return control valve
(ball valve) 17.During test run, the oil-in of the first engine hydraulic pump b2, the oil-in difference of the second engine hydraulic pump b3
It is connected with described first in-line, the second in-line, the oil-out of the first engine hydraulic pump, the second engine hydraulic pump
Oil-out be connected with the return line of hydraulic pump load station by snap joint 26 and pipe fitting respectively, and be connected to flow control valve
Before.
Various valves in the present embodiment, filter, effusion meter, Pressure gauge, snap joint etc. all can be bought by market.
Embodiment 2
In the present embodiment, can be used for structured flowchart such as Fig. 2 of the hydraulic pump load system of two kinds of type aero-engine ground runs
Shown in, hydraulic schematic diagram is as shown in Figure 5.Difference from Example 1 is that the first engine hydraulic pump b2 needs leakage of oil, test run
Time, the leak oil line joint 30 that the oil leakaging port of the first engine hydraulic pump is arranged with pressure oil tank 9 by pipe fitting is connected.
Embodiment 3
In the present embodiment, can be used for structured flowchart such as Fig. 3 of the hydraulic pump load system of two kinds of type aero-engine ground runs
Shown in, hydraulic schematic diagram is as shown in Figure 6.Difference from Example 1 is the first engine hydraulic pump b2 and the second engine liquid
Press pump b3 is required to leakage of oil, and during test run, the oil leakaging port of the first engine hydraulic pump and the oil leakaging port of the second engine hydraulic pump are respectively
The leak oil line joint 30 arranged with pressure oil tank 9 by pipe fitting is connected.
Claims (3)
1. can be used for a hydraulic pump load system for two kinds of type aero-engines ground run simultaneously, including hydraulic pump load station,
It is characterized in that being connected in parallel promising first engine hydraulic pump on the flowline of hydraulic pump load station provides the first oil-feed of pressure oil
Pipeline and the second in-line for the second engine hydraulic pump offer pressure oil, arranged on the return line of hydraulic pump load station
There is flow control valve；During test run, the oil-in of the first engine hydraulic pump, the second engine hydraulic pump oil-in respectively with institute
State the first in-line, the second in-line connects, the oil-out of the first engine hydraulic pump, the going out of the second engine hydraulic pump
Hydraulic fluid port is connected with the return line of hydraulic pump load station by snap joint and pipe fitting respectively, and before being connected to flow control valve.
Can be used for the hydraulic pump load system of two kinds of type aero-engines ground run simultaneously the most according to claim 1,
It is characterized in that the pressure oil tank of hydraulic pump load station is provided with leak oil line joint, during test run, the first engine hydraulic pump is or/and second
The leak oil line joint that the oil leakaging port of engine hydraulic pump is arranged with pressure oil tank by pipe fitting is connected.
The hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aero-engines the most according to claim 1 or claim 2,
It is characterized in that the structure of the first in-line and the second in-line is identical, successively by the first oil strainer (23), the second oil mistake
Filter (24) and oil-feed control valve (25) are connected in series composition by pipe fitting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410728490.7A CN104454690B (en) | 2014-12-03 | 2014-12-03 | Can be used for the hydraulic pump load system of two kinds of type aero-engines ground run simultaneously |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410728490.7A CN104454690B (en) | 2014-12-03 | 2014-12-03 | Can be used for the hydraulic pump load system of two kinds of type aero-engines ground run simultaneously |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104454690A CN104454690A (en) | 2015-03-25 |
| CN104454690B true CN104454690B (en) | 2016-08-24 |
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| CN201410728490.7A Active CN104454690B (en) | 2014-12-03 | 2014-12-03 | Can be used for the hydraulic pump load system of two kinds of type aero-engines ground run simultaneously |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106593968B (en) * | 2016-12-14 | 2018-01-16 | 成都发动机（集团）有限公司 | Hydraulic pump load control system for a machine double pump aero-engine ground run |
| CN111008480B (en) * | 2019-12-13 | 2023-05-23 | 湘潭大学 | Novel pump type selection method for centrifugal pump station energy expansion requirement |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU748043A1 (en) * | 1978-06-14 | 1980-07-15 | Предприятие П/Я В-8670 | Hydraulic-engine hydraulic synchronization system |
| RU2270989C1 (en) * | 2004-07-26 | 2006-02-27 | Открытое акционерное общество "АВТОВАЗ" | Technological system for suppressing aero-gas-dynamic noise of forced suck-out of exhaust gases of test subjects like wheeled vehicles equipped with internal combustion engines, or autonomous internal combustion engines of testing acoustic complex |
| CN201934424U (en) * | 2010-12-02 | 2011-08-17 | 中国南方航空工业(集团)有限公司 | Analog load hydraulic system of test aeroengine and pressure regulating device thereof |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN203584929U (en) * | 2013-11-04 | 2014-05-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Aero-engine test bay hydraulic pump load system |
| CN204344549U (en) * | 2014-12-03 | 2015-05-20 | 成都发动机（集团）有限公司 | Can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously |
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