CN205910007U - A zero loading device for aeroengine base bearing tester - Google Patents
A zero loading device for aeroengine base bearing tester Download PDFInfo
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- CN205910007U CN205910007U CN201620733306.2U CN201620733306U CN205910007U CN 205910007 U CN205910007 U CN 205910007U CN 201620733306 U CN201620733306 U CN 201620733306U CN 205910007 U CN205910007 U CN 205910007U
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Abstract
The utility model relates to a zero loading device for aeroengine base bearing tester, it sets up the shunt module between load mechanism and ratio pressure reducing valve, the shunt module includes pressure transmitter and solenoid valve, the solenoid valve includes the three -terminal at least, and load mechanism end pipeline, second section connection ratio pressure reducing valve end pipeline are connected to first end, the third section is connected and the return circuit oil tank, pressure transmitter is used for control the opening and closing of solenoid valve. The utility model discloses a zero loading device for aeroengine base bearing tester can easily realize can regarding as the external store system moreover from zero loaded test objective, under the condition that does not change former tester control system, makes current aeroengine base bearing tester all can possess zero year experimental ability on the bearing, has with low costs, the convenient advantage of repacking.
Description
Technical field
This utility model belongs to aeroplane engine main bearing zero and carries test field, and more particularly, to one kind is used for aero-engine
Zero loading equipemtn of base bearing exerciser.
Background technology
Aeroplane engine main bearing need to possess the ability bearing top load, and therefore aeroplane engine main bearing exerciser needs reality
The now examination to test bearing top load.Hydraulic loaded equipment be equipped with wide range proportioning valve come to realize to test bearing high load
Lotus loads.The range of proportioning valve is usually 10mpa, and dead band is 0～0.5mpa, and proportioning valve cannot be in stability contorting dead zone range
Hydraulic pressure.Therefore, exerciser loading equipemtn just cannot realize the zero load examination to test bearing.
Utility model content
The purpose of this utility model is to provide a kind of zero loading equipemtn for aeroplane engine main bearing exerciser, is used for
Solve the problems, such as that current loading equipemtn cannot be from zero loading.
For reaching above-mentioned purpose, the technical solution adopted in the utility model is: a kind of aeroplane engine main bearing that is used for tries
Test zero loading equipemtn of device, shunt module is set between load maintainer and proportional pressure-reducing valve, described shunt module includes
Pressure transmitter and electromagnetic valve, described electromagnetic valve at least includes three ends, and first end connects load maintainer end pipe road, second segment connects
Proportional pressure-reducing valve end pipe road, the 3rd section of connection and loop fuel tank, described pressure transmitter is used for controlling the unlatching of described electromagnetic valve
With closing.
Further, described electromagnetic valve is two-bit triplet electromagnetic valve.
Further, described load maintainer is axially loaded mechanism and/or radial loaded mechanism.
A kind of zero loading equipemtn for aeroplane engine main bearing exerciser of the present utility model can easily be realized from zero
The test objective loading, and existing boat can be made as external store system in the case of not changing former exerciser control system
Empty main bearing of engine exerciser all can possess the test capability of bearing zero load, have low cost, reequip convenient advantage.
Brief description
Accompanying drawing herein is merged in description and constitutes the part of this specification, show meet of the present utility model
Embodiment, and be used for explaining principle of the present utility model together with description.
Fig. 1 is the system of zero loading equipemtn for aeroplane engine main bearing exerciser of this utility model one embodiment
Schematic diagram.
Fig. 2 is zero load test on-load pressure dynamic changing curve of this utility model one embodiment.
Wherein, 1- load maintainer, 2- proportional pressure-reducing valve, 3- pressure transmitter, 4- pressure gauge, 5- hydraulic pump, 6- loop oil
Case, 10- separator module, 11- pressure transmitter, 12- electromagnetic valve.
Specific embodiment
For making purpose, technical scheme and advantage that this utility model is implemented clearer, below in conjunction with this utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in this utility model embodiment.In the accompanying drawings, ad initio
To the element that same or similar label represents same or similar element or has same or like function eventually.Described reality
Applying example is a part of embodiment of this utility model, rather than whole embodiments.Embodiment below with reference to Description of Drawings
It is exemplary type it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.New based on this practicality
Embodiment in type, the every other enforcement that those of ordinary skill in the art are obtained under the premise of not making the work of creation type
Example, broadly falls into the scope of this utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is described in detail.
In description of the present utility model it is to be understood that term " " center ", " longitudinal ", " horizontal ", "front", "rear",
The orientation of instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " or position relationship are based on accompanying drawing institute
The orientation showing or position relationship, are for only for ease of description this utility model and simplify description, rather than instruction or hint indication
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The restriction of novel protected scope.
The system being illustrated in figure 1 zero loading equipemtn for aeroplane engine main bearing exerciser of the present utility model is former
Reason figure, for solving the problems, such as that exerciser loading equipemtn cannot realize zero loading, transforms to former hydraulic loaded pipeline, sets former
Shunt module 10 is added, specifically, former hydraulic loaded management provides power by hydraulic pump 5, by two in standby loading oil circuit
Group proportional pressure-reducing valve 2 and pressure transmitter 3 connect two load maintainers 1 respectively, between hydraulic pump 5 and proportional pressure-reducing valve 2 also
There is pressure gauge, shunt module 10 is set between load maintainer 1 and proportional pressure-reducing valve 2, shunt module 10 includes pressure and becomes
Send device 11 and electromagnetic valve 12, electromagnetic valve 12 at least includes three ends, first end connects load maintainer end pipe road, second segment connects ratio
Air relief valve end pipe road, the 3rd section of connection and loop fuel tank 6, pressure transmitter 11 is used for controlling the open and close of electromagnetic valve 12.
Preferably, two-bit triplet electromagnetic valve selected by electromagnetic valve 12.
It should be noted that as shown in FIG. 1, the afterburning part that the load maintainer 1 in left side stretches out is horizontal (level side
To) it is laterally loading framework, the afterburning part that the loading framework 1 on right side stretches out is that radially (vertical method) is radial loaded
Mechanism, load maintainer 1 both can be arranged between axially loaded mechanism and proportional pressure-reducing valve 2, can also be in radial loaded mechanism
Arrange and proportional pressure-reducing valve 2 between, can also be in the corresponding proportional pressure-reducing valve 2 of axially loaded mechanism and radial loaded mechanism
Between be respectively provided with.
Below to arrange diverter shown in this specification accompanying drawing 1 between horizontal load maintainer and proportional pressure-reducing valve 2
Module 10 is further elaborated.
Adopt hydraulic loaded mode the load mode of aeroplane engine main bearing exerciser more, and the change of loaded load is
Passing ratio air relief valve to be realized to the regulation of hydraulic pressure.But proportional pressure-reducing valve exists in the case of pressure is less
" dead band ", therefore, this system cannot realize zero load in bearing test.
Carry test to hydraulic loaded pipeline transformation for carrying out bearing zero, the loading oil circuit of original equipment arranges separator mould
Block 10.Two-position three way magnetic valve (two-position three way magnetic valve response time: ton=25ms, toff=is installed in separator module 10
10ms) with pressure transmitter 11.By being controlled to the opening/closing time of two-position three way magnetic valve using independent unloading control system
System realizes the fast discharging of loading system, and schematic diagram is as shown in Figure 1.
When electromagnetic valve 12 power-off, loading oil circuit is in connected state, axial load normal load；When electromagnetic valve 12 is energized
When, load oil feed line and be in cut-off state, load cylinder link circuit fuel tank 6 and air conducting, using in oil cylinder and air
Between pressure reduction quickly axial load is offloaded to zero.During test, by the pressure transducer of the axially loaded oil circuit front end of monitoring
Reflecting the situation of change of bearing axial force, pressure is zero to think that axial load is zero to situation.
By unloading control system, the precise control of two position, three-way electromagnetic change valve is realized with the fast discharging of loading system,
Thus realizing bearing zero load, during obtaining zero load by data actuation, on-load pressure change curve is as shown in Figure 2.
Zero loading equipemtn for aeroplane engine main bearing exerciser of the present utility model can easily be realized from zero loading
Test objective, and existing aviation can be made as external store system in the case of not changing former exerciser control system to send out
Motivation base bearing exerciser all can possess the test capability of bearing zero load, have low cost, reequip convenient advantage.
The above, optimum specific embodiment only of the present utility model, but protection domain of the present utility model is not
It is confined to this, any those familiar with the art, in the technical scope that this utility model discloses, can readily occur in
Change or replacement, all should cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with
Described scope of the claims is defined.
Claims (3)
1. a kind of zero loading equipemtn for aeroplane engine main bearing exerciser it is characterised in that load maintainer (1) with than
Setting shunt module (10) between example air relief valve (2), described shunt module (10) includes pressure transmitter (11) and electromagnetism
Valve (12), described electromagnetic valve (12) at least includes three ends, and first end connects load maintainer end pipe road, second segment connects ratio decompression
Valve end pipe road, the 3rd section of connection and loop fuel tank (6), described pressure transmitter (11) is used for controlling opening of described electromagnetic valve (12)
Open and close.
2. zero loading equipemtn for aeroplane engine main bearing exerciser according to claim 1 is it is characterised in that institute
Stating electromagnetic valve (12) is two-bit triplet electromagnetic valve.
3. zero loading equipemtn for aeroplane engine main bearing exerciser according to claim 1 is it is characterised in that institute
Stating load maintainer (1) is axially loaded mechanism and/or radial loaded mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620733306.2U CN205910007U (en) | 2016-07-12 | 2016-07-12 | A zero loading device for aeroengine base bearing tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620733306.2U CN205910007U (en) | 2016-07-12 | 2016-07-12 | A zero loading device for aeroengine base bearing tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205910007U true CN205910007U (en) | 2017-01-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620733306.2U Active CN205910007U (en) | 2016-07-12 | 2016-07-12 | A zero loading device for aeroengine base bearing tester |
Country Status (1)
| Country | Link |
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| CN (1) | CN205910007U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109519446A (en) * | 2017-09-20 | 2019-03-26 | 吉林省海格力斯自动化设备制造有限公司 | Simple mould hydraulic device |
-
2016
- 2016-07-12 CN CN201620733306.2U patent/CN205910007U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109519446A (en) * | 2017-09-20 | 2019-03-26 | 吉林省海格力斯自动化设备制造有限公司 | Simple mould hydraulic device |
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| GR01 | Patent grant |