CN203203787U - Aeroengine high pressure compressor first order disc fatigue circulating test apparatus - Google Patents
Aeroengine high pressure compressor first order disc fatigue circulating test apparatus Download PDFInfo
- Publication number
- CN203203787U CN203203787U CN 201320154938 CN201320154938U CN203203787U CN 203203787 U CN203203787 U CN 203203787U CN 201320154938 CN201320154938 CN 201320154938 CN 201320154938 U CN201320154938 U CN 201320154938U CN 203203787 U CN203203787 U CN 203203787U
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- pressure compressor
- central shaft
- testpieces
- test
- supporting disk
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Abstract
The utility model relates to an aeroengine high pressure compressor first order disc fatigue circulating test apparatus installed on a tester, comprising a testpiece, a simulation member and a test tool. The test tool comprises a support disc and a central shaft; the disc center of the support disc is in sliding fit with the central shaft; the central shaft is in connection with a main shaft of the tester; the testpiece and the simulation member are respectively in connection with the support disc; an elastic element is arranged between the support disc and the central shaft. The aeroengine high pressure compressor first order disc fatigue circulating test apparatus has a compact structure and is convenient to install; in order to simulate real displacement under the condition of an engine, an elastic element is arranged between the support disc and the central shaft; buffer is added between the support disc and the central shaft, which guarantees that testpiece displacement is amount to the displacement under the condition of an engine; an appropriate elastic element can be flexibly chosen in dependence on the testpiece; the aeroengine high pressure compressor first order disc fatigue circulating test apparatus is simple to operate and is convenient to adjust and solves the problem that the credibility of a reserved safe circulating life provided by a present test method is not high and use hidden trouble exists.
Description
Technical field
The utility model relates to aeromotor test field, specifically, relates to a kind of test unit for simulation aeromotor high-pressure compressor one-level dish actual working state.
Background technology
It is the heart of aircraft that aeromotor is described as, and for guaranteeing flight safety, requires engine to have high safety in utilization and dependability.But because the abominable of engine operation environment has fault to take place in the time of in real work, some in addition can cause fatal crass's serious consequence.
High-pressure compressor one-level dish is as one of critical component of aeromotor, has crucial effects for structural intergrity and the dependability of engine, in case high-pressure compressor one-level dish operational failure just might cause a serious accident.Institute thinks assurance use safety, must provide its predetermined safe cycle life by test.And whether the predetermined safe cycle life that test provides is credible and reliable, and test unit reasonable in design is key link wherein.Though did such test abroad, owing to relate to core technology, all externally highly confidential, China can't obtain the reference of its test method and test unit at all.Domesticly equally also did certain trial, but because the special construction of high-pressure compressor one-level dish, when its work, be subjected to influencing its rim section and can producing certain displacement in the axial direction of centrifugal force, also can't simulate this axial displacement at present, make that trystate and actual working state are not quite identical, it is not high to cause testing the predetermined safe cycle life confidence level that provides, and exists to use potential safety hazard.
The utility model content
The purpose of this utility model is to use the problems referred to above such as safety because of the not high existence of predetermined safe cycle life confidence level that provides at high-pressure compressor when working, a kind of aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit is provided, this test unit can be used in the real work situation of simulated high-pressure pneumatic plant one-level dish, for solve the predetermined safe cycle life confidence level that existing test method provides not high, exist the problem of use potential safety hazard that research technique is provided.
The technical solution of the utility model is: a kind of aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit, be installed on the exerciser, this device comprises testpieces, simulating piece and test frock, wherein, the test frock comprises supporting disk and central shaft, core and the central shaft of supporting disk are slidingly matched, and central shaft is connected with the main shaft of exerciser, and testpieces is connected with supporting disk respectively with simulating piece; Be provided with flexible member between supporting disk and the central shaft.
Preferably, flexible member is resilient ring, and this resilient ring is fixed on the central shaft.
Preferably, simulating piece comprises vane simulated, high-pressure compressor front axle simulating piece and high-pressure compressor rear axle simulating piece, wherein, vane simulated is installed on the testpieces, be used for the blade on the simulation test piece, high-pressure compressor front axle simulating piece connects testpieces and high-pressure compressor rear axle simulating piece, be used for the high-pressure compressor front axle of simulation test piece under engine condition, high-pressure compressor rear axle simulating piece is connected with supporting disk, is used for the high-pressure compressor rear axle of simulation test piece under engine condition.
Preferably, all be connected by test setoff part between testpieces and simulating piece and the supporting disk, this test setoff part comprises high pressure secondary dish, 1-2 level spacer ring and 2-3 level spacer ring, the inner spline housing tooth of high pressure secondary dish wheel hub and the engagement of the male splines of high-pressure compressor rear axle simulating piece cover tooth, 1-2 level spacer ring is installed between testpieces and the high pressure secondary dish by locating surface before and after it, and 2-3 level spacer ring is installed between high pressure secondary dish and the supporting disk by locating surface before and after it.
Preferably, testpieces is the high-pressure compressor one-level dish of testing.
The beneficial effects of the utility model are: the utility model test unit comprises testpieces, simulating piece and test frock, and testpieces is connected compact conformation, easy for installation with the test frock respectively with simulating piece; For real displacement under the simulated engine condition, be provided with flexible member between supporting disk and the central shaft, when the exerciser rotating speed increases to setting value gradually from zero, the distortion of testpieces wheel rim also increases thereupon and serves as a contrast or foil part by test, supporting disk transmits, because central shaft deflection very I is ignored, force the flexible member between supporting disk and the central shaft to deform, for increasing buffering between supporting disk and the central shaft, when deflection reaches displacement under the engine condition, supporting disk contacts fully with central shaft, can't continue distortion, guaranteed that the displacement of testpieces is identical with displacement under the engine condition, be that the tests of simulating state is consistent with engine behavior, and can select suitable flexible member flexibly according to testpieces, simple to operate, be easy to adjust, it is not high to have solved the predetermined safe cycle life confidence level that existing test method provides, there is the problem of using potential safety hazard.
Description of drawings
Fig. 1 is the utility model structural representation.
Fig. 2 is the structural representation of the utility model resilient ring.
Fig. 3 is the scheme of installation of the utility model on exerciser.
Wherein, 1, testpieces, 2, vane simulated, 3, high-pressure compressor front axle simulating piece, 4,1-2 level spacer ring, 5, high pressure secondary dish, 6,2-3 level spacer ring, 7, high-pressure compressor rear axle simulating piece, 8, supporting disk, 9, resilient ring, 10, central shaft, 11, the main shaft of exerciser, 12, the direct current drive unit, 13, gear speeder, 14, sealer, 15, vacuum tank, 16, two fulcrums of exerciser, 17, the two fulcrums of test, 18, the utility model test unit.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing.
A kind of aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit that the utility model provides, be installed on the exerciser, this device comprises testpieces 1, simulating piece and test frock, wherein, the test frock comprises supporting disk 8 and central shaft 10, the core of supporting disk 8 and central shaft 10 are slidingly matched, and central shaft 10 is connected with the main shaft 11 of exerciser, and testpieces is connected with supporting disk 8 respectively with simulating piece; Be provided with flexible member between supporting disk 8 and the central shaft 10, for increasing a buffering between supporting disk 8 and the central shaft 10, because testpieces 1 can be greater than the displacement under the engine condition at the displacement under the exerciser condition usually, be real displacement under the simulated engine condition, the flexible member that can select size to be fit to.
Above-mentioned flexible member adopts resilient ring 9, and this resilient ring 9 is fixed on the central shaft 10.
Performance for the testpieces under the true reflection aeromotor maximum (top) speed, above-mentioned simulating piece comprises vane simulated 2, high-pressure compressor front axle simulating piece 3 and high-pressure compressor rear axle simulating piece 7, wherein, be installed in for vane simulated 2 on the testpieces 1, be used for the real blade on the simulation test piece 1, its intensity can satisfy than the testing requirements under the higher rotating speed of aeromotor maximum (top) speed and not fragile, and its installation requirement is identical with the installation requirement of actual blade; High-pressure compressor front axle simulating piece 3 connects testpieces 1 and high-pressure compressor rear axle simulating piece 7, is used for the high-pressure compressor front axle of simulation test piece 1 under engine condition; High-pressure compressor rear axle simulating piece 7 is connected with supporting disk 8, is used for the high-pressure compressor rear axle of simulation test piece 1 under engine condition, and its its gearing of part that is connected with supporting disk drives whole armature spindle rotation.
In order to realize the accurately transmission stably of displacement between testpieces 1 and simulating piece and the supporting disk 8, all be connected by test setoff part between testpieces and simulating piece and the supporting disk 8, this test setoff part comprises high pressure secondary dish 5,1-2 level spacer ring 4 and 2-3 level spacer ring 6, high pressure secondary dish 5 is the real secondary dish of engine, the male splines cover tooth engagement of the inner spline housing tooth of its wheel hub and high-pressure compressor rear axle simulating piece 7 guarantees centering and torsion pass; 1-2 level spacer ring 4 is the real spacer ring of engine, and is installed between testpieces 1 and the high pressure secondary dish 5 by locating surface before and after it; 2-3 level spacer ring 6 is the real spacer ring of engine, and is installed between high pressure secondary dish 5 and the supporting disk 8 by locating surface before and after it.
Above-mentioned testpieces 1 is the high-pressure compressor one-level dish of testing.
Above-mentioned flexible member can also adopt Crumple elements such as rubber spring or hydraulic spring grease cup.
Principle of work: after installing the utility model test unit 18 by above-mentioned annexation, its mode with cantilever is installed on the two fulcrums of test shown in Figure 3, and links to each other with two fulcrums of exerciser by shaft coupling.During test, drive the running of two-stage gear speeder motoring ring test rotor by the direct current drive unit, test is carried out under vacuum tank normal temperature state, for keeping vacuum state, goes out to be provided with sealer at vacuum tank test rotor outlet.When exerciser rotating speed shown in Figure 3 increased to setting value gradually from zero, the distortion of testpieces 1 wheel rim also increased thereupon and transmits backward by 1-2 level spacer ring 4, high pressure secondary dish 5,2-3 spacer ring 6, supporting disk 8.Because central shaft 10 deflections very I are ignored, force the resilient ring 9 between supporting disk 8 and the central shaft 10 to deform, when deflection reaches displacement under the engine condition, supporting disk 8 contacts fully with central shaft 10, can't continue distortion, thereby guaranteed that the displacement of testpieces 1 is identical with displacement under the engine condition, namely the tests of simulating state is consistent with engine behavior.
In addition, in order to ensure before off-test, not being damaged, should regularly replace resilient ring 9 according to actual conditions.
Claims (5)
1. aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit, be installed on the exerciser, it is characterized in that: this device comprises testpieces, simulating piece and test frock, the test frock comprises supporting disk and central shaft, core and the central shaft of supporting disk are slidingly matched, central shaft is connected with the main shaft of exerciser, and testpieces is connected with supporting disk respectively with simulating piece; Be provided with flexible member between supporting disk and the central shaft.
2. aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit according to claim 1, it is characterized in that: flexible member is resilient ring, and this resilient ring is fixed on the central shaft.
3. aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit according to claim 1, it is characterized in that: simulating piece comprises vane simulated, high-pressure compressor front axle simulating piece and high-pressure compressor rear axle simulating piece, wherein, vane simulated is installed on the testpieces, be used for the blade on the simulation test piece, high-pressure compressor front axle simulating piece connects testpieces and high-pressure compressor rear axle simulating piece, be used for the high-pressure compressor front axle of simulation test piece under engine condition, high-pressure compressor rear axle simulating piece is connected with supporting disk, is used for the high-pressure compressor rear axle of simulation test piece under engine condition.
4. aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit according to claim 1, it is characterized in that: all be connected by test setoff part between testpieces and simulating piece and the supporting disk, this test setoff part comprises high pressure secondary dish, 1-2 level spacer ring and 2-3 level spacer ring, the inner spline housing tooth of high pressure secondary dish wheel hub and the engagement of the male splines of high-pressure compressor rear axle simulating piece cover tooth, 1-2 level spacer ring is installed between testpieces and the high pressure secondary dish by locating surface before and after it, and 2-3 level spacer ring is installed between high pressure secondary dish and the supporting disk by locating surface before and after it.
5. according to any described aeromotor high-pressure compressor one-level dish fatigue and cyclic test unit of claim 1 to 4, it is characterized in that: testpieces is the high-pressure compressor one-level dish of testing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320154938 CN203203787U (en) | 2013-03-19 | 2013-03-19 | Aeroengine high pressure compressor first order disc fatigue circulating test apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320154938 CN203203787U (en) | 2013-03-19 | 2013-03-19 | Aeroengine high pressure compressor first order disc fatigue circulating test apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203203787U true CN203203787U (en) | 2013-09-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320154938 Expired - Lifetime CN203203787U (en) | 2013-03-19 | 2013-03-19 | Aeroengine high pressure compressor first order disc fatigue circulating test apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203203787U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104062105A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Fatigue cycling test device of first-stage disk of high-pressure compressor of aircraft engine |
| CN107725454A (en) * | 2017-10-28 | 2018-02-23 | 中航长沙设计研究院有限公司 | Two-spool compressor testing stand |
| CN109060339A (en) * | 2018-09-05 | 2018-12-21 | 中国航发动力股份有限公司 | A kind of experimental rig and method |
-
2013
- 2013-03-19 CN CN 201320154938 patent/CN203203787U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104062105A (en) * | 2013-03-19 | 2014-09-24 | 徐可君 | Fatigue cycling test device of first-stage disk of high-pressure compressor of aircraft engine |
| CN107725454A (en) * | 2017-10-28 | 2018-02-23 | 中航长沙设计研究院有限公司 | Two-spool compressor testing stand |
| CN109060339A (en) * | 2018-09-05 | 2018-12-21 | 中国航发动力股份有限公司 | A kind of experimental rig and method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130918 Effective date of abandoning: 20160817 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |