CN106053082A - Compressor testpieces and surge method thereof - Google Patents
Compressor testpieces and surge method thereof Download PDFInfo
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- CN106053082A CN106053082A CN201610372486.0A CN201610372486A CN106053082A CN 106053082 A CN106053082 A CN 106053082A CN 201610372486 A CN201610372486 A CN 201610372486A CN 106053082 A CN106053082 A CN 106053082A
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- test part
- compressor
- compressor test
- testpieces
- flexible connecting
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000012360 testing method Methods 0.000 claims abstract description 111
- 230000029058 respiratory gaseous exchange Effects 0.000 claims description 14
- 238000009434 installation Methods 0.000 abstract description 8
- 238000005457 optimization Methods 0.000 abstract description 3
- 238000010998 test method Methods 0.000 abstract 1
- 230000007246 mechanism Effects 0.000 description 11
- 238000013461 design Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000011144 upstream manufacturing Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 241000237858 Gastropoda Species 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Positive-Displacement Pumps (AREA)
Abstract
The present invention provides a compressor testpieces and a surge test method thereof. A mode of respectively fixing testpieces and an exhaust spiral case is employed, the testpieces and the exhaust spiral case are connected through a flexible connecting piece to avoid the overconstraint therebetween caused by each fixation. In order to avoid the danger of rupture caused by too-high internal pressure of the flexible connecting piece, the structure of the compressor testpieces is optimized. A bottleneck and an exhaust bypass outlet are added on the testpieces to allow the internal pressure of the flexible connecting piece to be located in a safe value rage at the surge test so as to avoid the rupture danger of the flexible connecting piece and ensure the safety of the surge test. The installation selection between the compressor testpieces and the exhaust spiral case is added through optimization of the compressor testpiece structure so as to reduce the installation difficulty. The surge method can be used on the testpieces with flexible connecting pieces, can be also used on compressor testpieces without weak link parts such as the flexible connecting pieces and the like, and has higher generality.
Description
Technical field
The present invention relates to engine art, in particular it relates to a kind of Compressor test part and force and breathe heavily method.
Background technology
Compressor is as one of big core component of aero-engine three, and its advance is directly connected to the skill of whole electromotor
Art level.In off-design behaviour, owing to air-flow has exceeded critical angle of attack to the angle of attack of blade, cause air-flow serious in blade is arranged
Separating, produce rotating stall, and then produce surge, this kind of phenomenon can make engine performance deterioration, can give the aircraft of high-speed flight
Cause serious consequence.
Therefore, whether the actual techniques parameter for checking compressor reaches to design requirement, needs to design Compressor test part
Make a service test.In performance test, the stall margin of compressor is to obtain a parameter.This parameter and common work
The relation making line determines the work that can whole electromotor safe.Stall margin needs by forcing Compressor test part
Breathe heavily test to obtain.
Current compressor is forced and is breathed heavily test and need to be joined directly together Compressor test part with exhaust volute, and spiral case is fixed on test run
On platform, it is desirable to Compressor test part is connected with each other with exhaust volute structure, force when breathing heavily test, go out by progressively closing off exhaust volute
Mouth valve, makes blower outlet back pressure gradually rise, and causes surge phenomenon.But Compressor test part phase direct with exhaust volute
Connect and the mode of each self-retaining easily causes Planar Mechanisms between the two, experiment requires height, installation difficulty to equipment conformability
Bigger.
Summary of the invention
The technical problem to be solved in the present invention is for existing Compressor test part and the technology of exhaust volute annexation
Not enough, it is provided that a kind of Compressor test part.
Another that the invention solves the problems that technical problem is that and provide a kind of forcing to breathe heavily the side of test based on described Compressor test part
Method.
The above-mentioned purpose of the present invention is achieved by the following technical programs:
Thering is provided a kind of Compressor test part, described Compressor test part connects exhaust volute, particular by adopting between
It is attached with connector.
The present invention takes mode Compressor test part, test bay exhaust volute fixed respectively, uses between
Connector connects, and arranges after connector is attached, can effectively prevent because each self-retaining causes Planar Mechanisms between the two.
If using rigid connector to be connected between Compressor test part with test bay exhaust volute, installation difficulty is relative
Bigger, it is difficult to ensure the axle center alignment between installed part, and Planar Mechanisms between union piece can be caused, to Compressor test part at ride
Installation, test tape serve unfavorable factor.So, the preferred described connector of the present invention is thin-walled, the flexibly connecting of poor rigidity
Part.Described flexible connecting member uses thin-walled, the material of poor rigidity, can be better protected from the Compressor test part at connector two ends with
Produce Planar Mechanisms between test bay exhaust structure, and add the selectivity installed between Compressor test part and exhaust volute,
Substantially reduce installation difficulty.
Further, the present invention is provided with venturi in one end of described Compressor test part at flexible connecting member, described
Venturi is flow restriction.
Preferably, at flexible connecting member, exit casing, described aerofluxus it are provided with in one end of described Compressor test part
Being provided with venturi inside casing, venturi is flow restriction.
Described exit casing is provided with discharge bypass outlet away from one end of flexible connecting member；The outlet of described discharge bypass is provided with
On-off control valve.
The size of described venturi matches with testpieces；Depending on the size of venturi is according to testpieces concrete condition, its test
The position of part can determine according to the specific constructive form of the part that testpieces flexible connecting member is connected, described throat structure
Can be, but not limited to use vane type, a board-like or version of current limiting plate.
Flexible structure is set between Compressor test part and exhaust volute, can solve well because of Compressor test part
Self-retaining each with exhaust volute causes Planar Mechanisms problem between the two.According to operating characteristic during compressor surge, testpieces
The internal pressure of exhaust volute upstream part can be increased dramatically, and flexible connecting member is in exhaust volute upstream, may exist because of
Internal pressure is too high and the risk ruptured occurs, and affects experimental safe to a certain extent.For avoiding Compressor test part, aerofluxus snail
There is the risk occurring rupturing, the present invention knot to Compressor test part because internal pressure is too high in the flexible connecting member between shell
The further scientific optimization of structure, is provided with venturi in one end of described Compressor test part at flexible connecting member, and venturi is limited
Flow structure, exit casing is provided with discharge bypass outlet away from one end of flexible connecting member.Based on new structure, Compressor test part
Carry out forcing breathe heavily test time, discharge bypass outlet switch progressively close off or reduce, venturi is near Compressor test part one end
Inside parts pressure, relatively forces and gradually rises before breathing heavily test；Venturi, near the inside parts pressure of flexible connecting member one end, is relatively forced and is breathed heavily
Before test, change is little；I.e. pressure within flexible connecting member is constantly in safety value, avoids the broken of flexible connecting member well
Split risk, it is ensured that force the safety breathing heavily test.
Further, for there is no the Compressor test part of the weak link parts such as flexible connecting member, it is also possible to arrange larynx
Road structure, the optional position connecting exhaust volute one end at Compressor test part can be designed in the position of described venturi.
Further, the outlet of described discharge bypass is arranged on Compressor test part, is positioned at exit casing away from flexibility even
One end of fitting, its position should not affect testpieces outlet parameter and measure the measurement of point, in the case of structure allows, Ying Jinke
Point can be measured away from outlet parameter.If discharge bypass outlet is positioned close to parameter measurement point, near discharge bypass outlet
Air draught is not sufficiently stable, and the data measuring some collection cannot truly reflect practical situation, affects result of the test, it is difficult to accurately survey
Determine stall margin.
Further, described discharge bypass outlet size can be according to the charge flow rate of Compressor test part and throat area
Fixed, discharge bypass export volume can use single or multiple.
Further, described on-off control valve is drawn from testpieces, is arranged on discharge bypass exit, and its position can
With flexible arrangement, it is not limited to the method being arranged at volute outlet of routine.Described on-off control valve is used for controlling to force breathing heavily
Compressor test part outlet back pressure in test, closes or turns down on-off control valve and i.e. close or turn down discharge bypass outlet, meeting
Make testpieces outlet back pressure raise, and then make compressor surge.
Based on described Compressor test part, the present invention forces the method breathing heavily test, first Compressor test part to be sucked by gas
Inside testpieces, by progressively closing off or turn down the on-off control valve of discharge bypass outlet, make testpieces outlet back pressure gradually
Raise, until surge, after gathering test data, discharge bypass outlet is opened.Force and breathe heavily in test, Compressor test part and test run
Planar Mechanisms problem is there is not between platform exhaust volute.
And it being provided with the testpieces of throat structure, venturi raises away from the testpieces internal pressure of flexible connecting member, venturi
The connector connected is little with the inside parts pressure change of exhaust volute, and flexible connecting member internal pressure is constantly in safety
Value, can eliminate flexible connecting member because of during test internal pressure too high and the risk ruptured occurs, be further ensured that experimental safe
Carry out.
In sum, the invention provides a kind of Compressor test part and force and breathe heavily method, use Compressor test part with
Exhaust structure is separately fixed on test bay, and is connected by flexible connecting member；Compressor test part sets near connector one end
Having venturi, venturi to be arranged on inside exit casing, venturi size matches with Compressor test part, and exit casing is away from flexibility even
One end of fitting is provided with discharge bypass outlet；Discharge bypass outlet is provided with on-off control valve.Force when breathing heavily test, arranged by control
The on-off control valve of gas bypass outlet, makes blower outlet back pressure gradually rise, until surge, obtains testpieces surge number
According to.
The method have the advantages that
The present invention, by optimizing the structure of Compressor test part, adds flexible connecting member between testpieces and exhaust volute structure
Connect, it is to avoid the Planar Mechanisms produced in assembling between testpieces and exhaust volute structure.
Stud connector design is flexible connecting member by the present invention further, expands Compressor test part and exhaust volute device
Between install selectivity, reduce installation difficulty.
Yet further, the present invention arranges the venturi of protection flexible connecting member at testpieces and flexible connecting member connecting portion
And discharge bypass outlet, it is ensured that force the safety breathing heavily test, and compared with forcing with routine and breathing heavily method, method is breathed heavily in forcing of the present invention
May be used for having on the testpieces of flexible connecting member, it is also possible to for there is no the compressor of the weak link parts such as flexible connecting member
Testpieces, has higher versatility.
Accompanying drawing explanation
The Figure of description of the part constituting the application is used for providing a further understanding of the present invention, and the present invention shows
Meaning property embodiment and explanation thereof are used for explaining the present invention, are not intended that inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is Compressor test part and exhaust volute attachment structure schematic diagram.
Fig. 2 is venturi support plate schematic diagram.
In Fig. 1,201 is air flow, and 301 is exhaust volute, and 401 is flexible connecting member, and 501 is exit casing 1,502
For venturi support plate, 601 export for discharge bypass.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but what the present invention can express with this specification
The multitude of different ways that design philosophy limited and covered is implemented.
For exempting to repeat, illustrate with preferred embodiment below.
As it is shown in figure 1, the Compressor test part that the present invention provides is connected 301 by flexible connecting member 401 with exhaust volute
Connecting, Compressor test part and exhaust volute are separately fixed on test ride, and exit casing 501 is the one of Compressor test part
Part, is bolted on Compressor test part.Compressor test part is provided with exhauster near flexible connecting member 401 one end
Casket 501, described exit casing 501 is internal is provided with venturi 502, and venturi 502 is made up of the plank frame that circumference is uniform；Described row
Mechanism of qi casket 501 is provided with discharge bypass outlet 601 away from one end of flexible connecting member 401；Described discharge bypass outlet 601 is provided with out
Close and control valve.
In the embodiment of the present invention, Compressor test part throat area is 2700mm2, throat area support plate number is 20, week
In being distributed on exit casing 501, support plate place radius 170 ~ 180mm, discharge bypass outlet has at 5 ~ 7, each discharge bypass
Discharge area is identical is 240 ~ 280 mm2, discharge bypass outlet everywhere is compiled at 1 after drawing, and uses 1 Valve controlling bypass
Switch.
If testpieces is connected by the part that rigidity is bigger with exhaust volute 301, the technical problem of Planar Mechanisms between the two
Solve the most thorough.The flexible connecting member 401 using thin-walled, rigidity weak the most between the two connects.Can the company of being better protected from
Between Compressor test part and the test bay exhaust structure at fitting two ends produce Planar Mechanisms, and expand Compressor test part with
The selectivity installed between exhaust volute, substantially reduces installation difficulty.
Flexible structure is set between Compressor test part and exhaust volute, can solve well because of Compressor test part
Self-retaining each with exhaust volute causes Planar Mechanisms problem between the two.Compressor test part according to conventional method by by
Step is closed the valve of exhaust volute outlet and is carried out forcing when breathing heavily test, and the internal pressure of testpieces exhaust volute upstream part can be drastically
Increasing, flexible connecting member is in exhaust volute upstream, may there is the risk occurring rupturing because internal pressure is too high, necessarily
Experimental safe is affected in degree.For avoiding the flexible connecting member between Compressor test part, exhaust volute to exist because of internal pressure
Too high and the risk ruptured occurs, the present invention further scientific optimization of structure to Compressor test part, try at described compressor
The one end testing part is provided with venturi at flexible connecting member, and venturi is flow restriction；Exit casing is away from flexible connecting member
One end is provided with discharge bypass outlet, and discharge bypass outlet can be switched by valve.Based on new structure, Compressor test
Part carry out forcing breathe heavily test time, by gradually walk closedown or reduce discharge bypass export, make testpieces outlet back pressure raise, test
Inside part, venturi, near the inside parts pressure of Compressor test part one end, is relatively forced and is gradually risen before breathing heavily test；Venturi is near soft
Property connector one end inside parts pressure, relatively force change before breathing heavily test little；I.e. pressure within flexible connecting member is located always
In safety value, avoid the risk of rupture of flexible connecting member well, it is ensured that force the safety breathing heavily test.
It is provided with a plank frame of current limliting in flexible connecting member 401 and testpieces junction, hinders air-flow, breathe heavily reality forcing
During testing, by progressively closing or turn down discharge bypass outlet 601, the outlet back pressure of the inside of testpieces is made to be stepped up,
And at flexible connecting member and exhaust volute 301 inside parts pressure with force breathe heavily experiment before change little, flexible connecting member is located always
In safety range, do not have the risk ruptured.Add and force the safety breathing heavily process of the test.
Present configuration, through actual analysis and experimental examination, can solve asking of this area Compressor test part well
Topic, can apply to other testpieces.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for those skilled in the art
For Yuan, the present invention can have various modifications and variations.All within the spirit and principles in the present invention, any amendment of being made,
Equivalent, improvement etc., within the scope of should be included in the comprising of the present invention.
Claims (9)
1. a Compressor test part, described Compressor test part is connected with exhaust volute structure, it is characterised in that described in calm the anger
Machine testpieces is fixed respectively with exhaust volute structure, and is connected by connector.
Compressor test part the most according to claim 1, it is characterised in that described connector is flexible connecting member.
Compressor test part the most according to claim 1 or claim 2, it is characterised in that one end of described Compressor test part is close
Being provided with venturi at connector, described venturi is flow restriction.
Compressor test part the most according to claim 3, it is characterised in that in one end of described Compressor test part near even
Being provided with exit casing at fitting, be provided with venturi inside described exit casing, venturi is flow restriction.
Compressor test part the most according to claim 3, it is characterised in that described exit casing is away from the one of flexible connecting member
End is provided with discharge bypass outlet；The outlet of described discharge bypass is provided with on-off control valve；The quantity of described discharge bypass outlet is
At least one.
6. according to Compressor test part described in claim 3,4 or 5, it is characterised in that described venturi be vane type, board-like or
Current limliting is board-like.
Compressor test part the most according to claim 5, it is characterised in that described discharge bypass exports at Compressor test part
Measure on the position of point away from outlet parameter.
Compressor test part the most according to claim 5, it is characterised in that described on-off control valve is by the row on testpieces
Draw at gas bypass outlet.
9. forcing of Compressor test part described in any one of a use right 1 ~ 8 breathes heavily method, it is characterised in that compressor tries
Test part to need to force when breathing heavily, by progressively closing off the on-off control valve of discharge bypass outlet, make Compressor test part outlet back pressure
Gradually rise, until surge；After gathering test data, discharge bypass outlet is opened, makes compressor exit surge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610372486.0A CN106053082B (en) | 2016-05-31 | 2016-05-31 | A kind of Compressor test part and its force asthma method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610372486.0A CN106053082B (en) | 2016-05-31 | 2016-05-31 | A kind of Compressor test part and its force asthma method |
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| Publication Number | Publication Date |
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| CN106053082A true CN106053082A (en) | 2016-10-26 |
| CN106053082B CN106053082B (en) | 2019-08-30 |
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| CN201610372486.0A Active CN106053082B (en) | 2016-05-31 | 2016-05-31 | A kind of Compressor test part and its force asthma method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112067302A (en) * | 2020-09-17 | 2020-12-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Surge pressure signal measuring structure for aircraft engine |
| CN112324695A (en) * | 2020-11-03 | 2021-02-05 | 中国航发沈阳发动机研究所 | Compressor surge method |
| CN114323652A (en) * | 2020-09-28 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Exhaust and gas collection device of axial flow compressor tester |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112067302A (en) * | 2020-09-17 | 2020-12-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Surge pressure signal measuring structure for aircraft engine |
| CN112067302B (en) * | 2020-09-17 | 2022-10-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Surge pressure signal measuring structure for aircraft engine |
| CN114323652A (en) * | 2020-09-28 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Exhaust and gas collection device of axial flow compressor tester |
| CN114323652B (en) * | 2020-09-28 | 2023-10-13 | 中国航发商用航空发动机有限责任公司 | Exhaust and gas collection device of axial-flow compressor tester |
| CN112324695A (en) * | 2020-11-03 | 2021-02-05 | 中国航发沈阳发动机研究所 | Compressor surge method |
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| Publication number | Publication date |
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| CN106053082B (en) | 2019-08-30 |
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Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |