CN104454690A - Hydraulic pump loading system for simultaneously performing ground test on two types of aero-engines - Google Patents
Hydraulic pump loading system for simultaneously performing ground test on two types of aero-engines Download PDFInfo
- Publication number
- CN104454690A CN104454690A CN201410728490.7A CN201410728490A CN104454690A CN 104454690 A CN104454690 A CN 104454690A CN 201410728490 A CN201410728490 A CN 201410728490A CN 104454690 A CN104454690 A CN 104454690A
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- Prior art keywords
- hydraulic pump
- oil
- line
- engine
- pump load
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Classifications
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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)
- Fluid-Pressure Circuits (AREA)
- Supply Devices, Intensifiers, Converters, And Telemotors (AREA)
Abstract
The invention discloses a hydraulic pump loading system for simultaneously performing a ground test on two types of aero-engines. The hydraulic pump loading system comprises a hydraulic pump loading station, wherein a first oil inlet pipeline for providing pressure oil to a first engine hydraulic pump and a second oil inlet pipeline for providing pressure oil to a second engine hydraulic pump are connected to an oil outlet tube of the hydraulic pump loading station in parallel, and a flow rate regulating valve is arranged on the oil returning pipeline of the hydraulic pump loading station; during test run, the oil inlet of the first engine hydraulic pump and the oil inlet of the second engine hydraulic pump are respectively connected to the first oil inlet pipeline and the second oil inlet pipeline, and an oil outlet of the first engine hydraulic pump and an oil outlet of the second engine hydraulic pump are respectively connected to the oil returning pipeline of the hydraulic pump loading station by virtue of a quick joint and a tube fitting, and are connected in front of the flow rate regulating valve.
Description
Technical field
The invention belongs to aeroengine ground run technical field, the oil hydraulic pump load system of particularly aeroengine ground run.
Background technique
Domestic existing aircraft engine test stand frame is all that a kind of model motor uses a set of its Test Rig, in manufacturing equipment, is also that a kind of model motor uses a set of oil hydraulic pump load system, and can not carries out test run to two motors simultaneously.Thus there is following problem: 1, the motor of often kind of model must have corresponding oil hydraulic pump load system, and thus the quantity of oil hydraulic pump load system constantly increases, the fund expended and land resources increase, and the cost of production of motor improves.2, test run can not be carried out to two motors simultaneously, affect test run efficiency.
Summary of the invention
The object of the invention is to overcome the deficiencies in the prior art, a kind of oil hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aeroengines is provided, to economize on resources, reduces costs, improve test run efficiency.
The oil hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aeroengines of the present invention, comprise oil hydraulic pump load station, the oil outlet tube of oil hydraulic pump load station is connected in parallel promising first engine hydraulic pump the first in-line of pressure oil is provided and provides the second in-line of pressure oil for the second engine hydraulic pump, the return line of oil hydraulic pump load station is provided with flow control valve; During test run, the filler opening of the first engine hydraulic pump, the filler opening of the second engine hydraulic pump are connected with described first in-line, the second in-line respectively, the oil outlet of the first engine hydraulic pump, the oil outlet of the second engine hydraulic pump are connected with the return line of oil hydraulic pump load station respectively by rapid pipe joint and pipe fitting, and before being connected to flow control valve.
The oil hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aeroengines of the present invention, the pressure oil tank of its oil hydraulic pump load station is provided with leak oil line joint, during test run, if engine hydraulic pump needs leakage of oil, then the leak oil line joint that the oil leakaging port of engine hydraulic pump is arranged by pipe fitting and pressure oil tank can be connected, if engine hydraulic pump does not need leakage of oil, then the leak oil line joint that pressure oil tank can be arranged cuts out.
The oil hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aeroengines of the present invention, its first in-line is identical with the structure of the second in-line, to be connected in series successively to form by the first oil strainer, the second oil strainer and oil-feed control valve by pipe fitting.
The present invention has following beneficial effect:
1, because the oil hydraulic pump load station in oil hydraulic pump load system of the present invention is connected in parallel to the first in-line and the second in-line on oil outlet tube, return line is provided with flow control valve, thus achieve a set of oil hydraulic pump load system and can carry out ground run for the motor of two kinds of types, and test run can be carried out to two motors simultaneously.
2, because a set of oil hydraulic pump load system can carry out ground run for the motor of two kinds of types, and test run can be carried out to two motors simultaneously, thus not only can economize on resources, reduce costs, and test run efficiency can be improved.
3, carry out ground run to aeroengine, stability of flow with oil hydraulic pump load system of the present invention, controlling is good, can ensure test run quality completely.
Accompanying drawing explanation
Fig. 1 is the first structured flowchart that can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously of the present invention;
Fig. 2 is the second structured flowchart that can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously of the present invention;
Fig. 3 is the third structured flowchart that can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously of the present invention;
Fig. 4 is the first hydraulic schematic diagram that can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously of the present invention;
Fig. 5 is the second hydraulic schematic diagram that can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously of the present invention;
Fig. 6 is the third hydraulic schematic diagram that can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously of the present invention.
In figure, 1-gas cylinder, 2-reduction valve, 3-air filter, 4-needle value, 5-gas exhausting valve (FERRULETYPE ball valve), 6-safety valve, 7-funnel, 8-refueling control valve (ball valve), 9-pressure oil tank, 10-go out oil control valve (ball valve), 11-heat exchanger, 12-water supply control valve (solenoid valve), 13-level meter, 14-relief valve, 15-leading hydraulic control one-way valve, 16-Cross fade wet solenoid valve, 17-oil return control valve (ball valve), 18-throttle valve, 19-first-class gauge (turbine flowmeter), 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-rapid pipe joint, 27-the three oil strainer, 28-accumulator, 29-water-returning control valve (ball valve), 30-leak oil line joint, 31-blowdown control valve, b1-oil hydraulic pump load station, b2-the first engine hydraulic pump, b3-the second engine hydraulic pump.
Embodiment
Also by reference to the accompanying drawings the oil hydraulic pump load system that can be used for the ground run simultaneously of two kinds of type aeroengines of the present invention is described further below by embodiment.
Embodiment 1
In the present embodiment, can be used for the structured flowchart of the oil hydraulic pump load system of two kinds of type aeroengines ground run as shown in Figure 1, hydraulic schematic diagram as shown in Figure 4, comprise oil hydraulic pump load station b1, the oil outlet tube of oil hydraulic pump load station is connected in parallel promising first engine hydraulic pump the first in-line of pressure oil is provided and provides the second in-line of pressure oil for the second engine hydraulic pump, the return line of oil hydraulic pump load station is provided with flow control valve.
As can be seen from Figure 4, oil hydraulic pump load station b1 comprises pressure oil tank 9, pressure oil tank 9 be connected with gas cylinder 1, reduction valve 2, air filter 3, needle value 4 form add pressure gas channel, the gas exhaust piping of gas exhausting valve (FERRULETYPE ball valve) 5, safety valve 6 composition, the filling conduit of funnel 7, refueling control valve (ball valve) 8 composition, drain the oil blowoff line and leak oil line joint 30 that pipe fitting and blowdown control valve (ball valve) 31 form; First in-line in parallel on the oil outlet tube of oil hydraulic pump load station b1, the second oil inlet pipeline structure are identical, to be connected in series successively to form by the first oil strainer 23, second oil strainer 24 and oil-feed control valve (ball valve) 25 by pipe fitting; The flow control valve that the return line of oil hydraulic pump load station b1 is arranged is connected in parallel by three groups and forms, often organize flow control valve to form by leading hydraulic control one-way valve 15, Cross fade wet solenoid valve and throttle valve 18, after flow control valve, also be provided with relief valve 14, the return tube in parallel with flow control valve be also provided with oil return control valve (ball valve) 17.During test run, the filler opening of the first engine hydraulic pump b2, the filler opening of the second engine hydraulic pump b3 are connected with described first in-line, the second in-line respectively, the oil outlet of the first engine hydraulic pump, the oil outlet of the second engine hydraulic pump are connected with the return line of oil hydraulic pump load station respectively by rapid pipe joint 26 and pipe fitting, and before being connected to flow control valve.
Various valves, filter, flowmeter, pressure gauge, rapid pipe joint etc. in the present embodiment are all bought by market.
Embodiment 2
In the present embodiment, can be used for the structured flowchart of the oil hydraulic pump load system of two kinds of type aeroengines ground run as shown in Figure 2, hydraulic schematic diagram as shown in Figure 5.Difference from Example 1 is that the first engine hydraulic pump b2 needs leakage of oil, and during test run, the leak oil line joint 30 that the oil leakaging port of the first engine hydraulic pump is arranged by pipe fitting and pressure oil tank 9 is connected.
Embodiment 3
In the present embodiment, can be used for the structured flowchart of the oil hydraulic pump load system of two kinds of type aeroengines ground run as shown in Figure 3, hydraulic schematic diagram as shown in Figure 6.Difference from Example 1 is that the first engine hydraulic pump b2 and the second engine hydraulic pump b3 all need leakage of oil, during test run, the leak oil line joint 30 that oil leakaging port and second engine hydraulic pump of the first engine hydraulic pump are arranged respectively by pipe fitting and pressure oil tank 9 is connected.
Claims (3)
1. one kind can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously, comprise oil hydraulic pump load station, it is characterized in that being connected in parallel promising first engine hydraulic pump on the oil outlet tube of oil hydraulic pump load station the first in-line of pressure oil to be provided and to provide the second in-line of pressure oil for the second engine hydraulic pump, the return line of oil hydraulic pump load station is provided with flow control valve; During test run, the filler opening of the first engine hydraulic pump, the filler opening of the second engine hydraulic pump are connected with described first in-line, the second in-line respectively, the oil outlet of the first engine hydraulic pump, the oil outlet of the second engine hydraulic pump are connected with the return line of oil hydraulic pump load station respectively by rapid pipe joint and pipe fitting, and before being connected to flow control valve.
2. can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously according to claim 1, it is characterized in that the pressure oil tank of oil hydraulic pump load station is provided with leak oil line joint, during test run, the first engine hydraulic pump is or/and the leak oil line joint that the oil leakaging port of the second engine hydraulic pump is arranged by pipe fitting and pressure oil tank is connected.
3. according to claim 1 or 2, can be used for the oil hydraulic pump load system of two kinds of type aeroengines ground run simultaneously, it is characterized in that the first in-line is identical with the structure of the second in-line, to be connected in series by pipe fitting by the first oil strainer (23), the second oil strainer (24) and oil-feed control valve (25) successively and to form.
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 true CN104454690A (en) | 2015-03-25 |
| CN104454690B CN104454690B (en) | 2016-08-24 |
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| Application Number | Title | Priority Date | Filing Date |
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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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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111008480A (en) * | 2019-12-13 | 2020-04-14 | 湘潭大学 | Newly-added pump model selection method for energy expansion requirement of centrifugal pump station |
Citations (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 |
-
2014
- 2014-12-03 CN CN201410728490.7A patent/CN104454690B/en active Active
Patent Citations (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 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111008480A (en) * | 2019-12-13 | 2020-04-14 | 湘潭大学 | Newly-added pump model selection method for energy expansion requirement of centrifugal pump station |
| CN111008480B (en) * | 2019-12-13 | 2023-05-23 | 湘潭大学 | Novel pump type selection method for centrifugal pump station energy expansion requirement |
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| Publication number | Publication date |
|---|---|
| CN104454690B (en) | 2016-08-24 |
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