CN110530750A - Abrasion tester under a kind of hot environment - Google Patents
Abrasion tester under a kind of hot environment Download PDFInfo
- Publication number
- CN110530750A CN110530750A CN201910746437.2A CN201910746437A CN110530750A CN 110530750 A CN110530750 A CN 110530750A CN 201910746437 A CN201910746437 A CN 201910746437A CN 110530750 A CN110530750 A CN 110530750A
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- CN
- China
- Prior art keywords
- insert
- testpieces
- bracket
- hot environment
- abrasion tester
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/56—Investigating resistance to wear or abrasion
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/0202—Control of the test
- G01N2203/0212—Theories, calculations
- G01N2203/0216—Finite elements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0222—Temperature
- G01N2203/0226—High temperature; Heating means
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses abrasion tester under a kind of hot environment, including electric furnace and vibration testing device, electric furnace is to divide half structure, and combination is enclosed in outside vibration testing device, and vibration testing device includes shake table, bracket and testpieces fixture；It, being capable of more true simulated engine turbo blade high-temperature work environment by this exerciser；The wear-resisting insert collision of turbine shroud can be simulated, abrasion, line contact wear is compressed and rotates the relationship under four kinds of operating conditions of scraped finish between the material of insert, surface roughness and pressing force and abrasion loss, finding influences the maximum factor of fretting wear, and test data support is provided for design, improvement aero-turbine integral shroud mechanism, and the different vibrational states of four kinds of energy simulated engine turbo blade, and corresponding wear pattern, maximum temperature is tested up to 1000 DEG C.
Description
Technical field
The invention belongs to aero-engine technology field, in particular to abrasion tester under a kind of hot environment.
Background technique
The design of aero engine turbine blades integral shroud has wear-resisting insert, plays damping effect.When first mounting turbine blades, phase
Adjacent wear-resisting insert is impaction state.But as abrasion loss increases, between adjacent insert pressing force reduce so that effectiveness in vibration suppression gradually under
Drop, and then lose damping capacity.The turbo blade for losing damping effect will be broken in the larger position of vibration stress, to aircraft
Safety causes a significant threat.Because turbo blade work is in 1000 DEG C or more of high-temperature fuel gas, efficiency test method there is no at present
Carry out approaching simulation.
Summary of the invention
Goal of the invention: to solve the above problems, the present invention devises abrasion tester under a kind of hot environment, the exerciser
It can be used as a kind of hot environment Imitating engine turbine integral shroud vibration damping insert fretting wear experimental rig.
Technical solution: abrasion tester under a kind of hot environment of the invention, including electric furnace and vibration testing device, electric furnace
To divide half structure, combination is enclosed in outside vibration testing device, and vibration testing device includes shake table, bracket and testpieces folder
Tool.
Further, on a vibration table, bracket includes left and right bearing, upper mounting base, insert bracket and for bracket installation
One insert, left and right support and mounting base are fixedly installed, and insert bracket is fixedly mounted on mounting base, the first insert and edge
The connection of block bracket.Wherein, above-mentioned bracket is installed on a vibration table by bolt, and left and right bearing, upper mounting base, insert bracket are logical
It crosses and is bolted installation.In addition, the first insert is fixedly connected with insert bracket by soldering.
Further, testpieces fixture is mounted in the vibration end of shake table, and testpieces fixture includes fixture base, test
Part mounting rack, testpieces compact heap, testpieces and the second insert, wherein fixture base is mounted in the vibration end of shake table, examination
It tests part installation and is erected at fixture base top, testpieces compact heap is bolted testpieces and is located at testpieces mounting rack
On, testpieces is connect with the second insert.
Further, fixture base includes front and back closure plate and dovetail groove, and testpieces mounting rack further includes adjusting nut and lock
Tight nut, dovetail groove are fixed by front and back closure plate, and testpieces mounting rack is mounted on dovetail groove, and pass through adjusting nut and locking screw
Mother is mobile and fixed in dovetail groove.
Further, the friction face contact of the first insert and the second insert.When 12 length of testpieces be 90-100mm, it is wide
When degree 13-15mm, thickness 2-4mm, two inserts contact of the invention is the most abundant, and effect is best.
Further, the position of corresponding first insert and the second insert is equipped with right-angle view window, the observation window above electric furnace
For quartz glass.
Advantageous effects: the present invention being capable of more true simulated engine turbo blade high-temperature work environment；It can
It simulates the wear-resisting insert collision of turbine shroud, compress abrasion, line contact wear and the material, the table that rotate insert under four kinds of operating conditions of scraped finish
Relationship between surface roughness and pressing force and abrasion loss finds the maximum factor of fretting wear that influences, and is design, improvement boat
Empty engine turbine integral shroud mechanism provides test data support.Compared with prior art, the present invention has the following obvious advantages:
(1) using four kinds of different vibrational states of cantilever beam vibration principle simulated engine turbo blade and corresponding abrasion
Mode；
(2) it is heated using electric furnace, simulated engine turbine shroud high-temperature work environment.Maximum temperature is tested up to 1000
℃；
(3) testpieces is simple rectangular section cantilever beam, is convenient for finite element stimulation.It can be tested, finite element is imitated
Analysis is mutually authenticated in true and analytic solutions.
Detailed description of the invention
Fig. 1 is appearance diagram of the invention；
Fig. 2 is structural schematic diagram of the invention；
Fig. 3 is vibration testing device structural schematic diagram of the invention；
Fig. 4 is vibration testing device structural exploded view of the invention；
Fig. 5 is testpieces clamp structure schematic diagram of the invention；
Fig. 6 is testpieces clamp structure exploded view of the invention；
Wherein, 1-electric furnace, 2-vibration testing devices, 3-brackets, 4-testpieces fixtures, 5-shake tables, 6-vertical
Observation window, 7-Zuo You bearings, 8-upper mounting bases, 9-M8 bolts, 10-insert brackets, the 11-the first insert, 12-examinations
Test part, 13-locking nuts, 14-adjusting nuts, 15-front and back closure plates, 16-fixture bases, 17-testpieces compact heaps,
18-testpieces mounting racks, 19-circlips, the 20-the second insert.
Specific embodiment
This part is the embodiment of the present invention, is used to help understand the purpose of the present invention and design.
Exerciser of the invention includes 2 two components of electric furnace 1 and vibration testing device.The electric furnace is conventional resistive furnace,
Divide half to design, can produce 1000 DEG C of hot environments.The vibration testing device 2 includes shake table 5, bracket 3 and testpieces fixture 4
Three parts.
Design has a right-angle view window 6 above the electric furnace 1, observation window design have quartz glass (it is heat-insulated, inside transparent visual
Material).
The bracket 3 is mounted on shake table 5 by M8 bolt 9, and bracket 3 includes left and right bearing 7, upper mounting base 8, edge
Block bracket 10 and insert 11.The left and right bracket 7 is connect by M8 bolt 9 with shake table 5.The upper mounting base 8 passes through M8
Bolt 9 is mounted in left and right bearing 7.The insert bracket 10 is mounted on mounting base 8 by M8 bolt 9.Described first
Insert 11 is brazed on insert bracket 10, and shake table can pass through the abrading motion of vibration simulation blade vibration.
The testpieces fixture 4 is mounted on shake table 5 by M8 bolt 9.
The testpieces fixture 4 includes fixture base 16, front and back closure plate 15, testpieces mounting rack 18, testpieces compact heap
17, adjusting nut 14, locking nut 13, testpieces 12 and the second insert 20 composition.Wherein front and back closure plate 15 and fixture base 16
9 are bolted by M8, the design of fixture base 16 has dovetail groove, and installation is all the testpieces mounting rack of dovetail configuration in dovetail groove
18.Testpieces mounting rack 18 is slided in dovetail groove by the rotation realization of adjusting nut 14.Adjusting nut 14 is fixed by circlip 19
Position.Testpieces mounting bracket 18 is realized fixed in dovetail groove by M6 clamping screw 13.Testpieces 12 is compressed by testpieces
Block 17 and M8 bolt (9) positioning and compression, testpieces mounting rack install the second insert of test, adjust the position of mounting rack
The first insert and the rubbing surface of the second insert is set to be connected, the second insert 20 is brazed on 12 top of testpieces.
Another embodiment of the invention is as follows.
Abrasion tester under a kind of hot environment, the testpieces fixture 4 and 10 material of insert bracket are GH2150,
Remaining part material is general stainless steel.
12 length of testpieces matrix is 95mm, width 14mm, thickness 3mm.Basis material is K465 high temperature alloy.Testpieces
The design of matrix one end has wear-resisting insert, and insert is having a size of 6mm × 3mm × 2mm.Insert material is K4208.Insert soldering is being tested
On part matrix and position is placed in the middle and concordant with testpieces matrix one end, insert 6mm length direction and testpieces matrix 14mm width
Direction is overlapped.
The assembling of testpieces fixture.By clamp structure schematic diagram assembling fixture shown in Fig. 5 and Fig. 6.
Extension elongation is 80mm after testpieces clamping.
The testpieces fixture 4 that will be completed, is mounted on shake table 5.By Fig. 3 and Fig. 4 mounting bracket 3.Wherein bracket 3
Insert identical with testpieces size is equally brazed on the insert bracket 10 for including, insert site is placed in the middle.
3 relative position of Adjustment Tests part fixture 4 and bracket, so that on insert 11 on testpieces 12 and insert bracket 10
Rubbing surface (Fig. 3) between insert 11 is overlapped.
In 12 two sides of testpieces matrix, foil gauge, foil gauge direction and testpieces length thereof are pasted apart from holding position 10mm
Direction is parallel, and position is placed in the middle.
Make to generate precompression between rubbing surface by adjusting nut 14.By testpieces under room temperature state FEM calculation
It learns, when the stress of foil gauge measurement is 652.7MPa, 787.4MPa and 877.8MPa, the normal pressure that generates between insert 11
For 200N, 300N and 400N.
By Fig. 1 and Fig. 2 installation electric furnace and fixation.
By 12 FEM calculation of testpieces, testpieces 1000 DEG C of next curved resonant frequencies be 259.2Hz and
1175.6Hz.One twist resonance frequency is 2705.3Hz.Corresponding to collision frequency in following table is 259.2Hz, and pressing friction frequency is
1175.6Hz, rotation scraped finish frequency are 2705.3Hz.Testpieces fixture 4 and 5 relative position of shake table are rotated 0.5 degree, and will
Input set of frequency is " line contact friction " test in 1408.1Hz, that is, analog following table.
Single laser measuring point is squeezed into downwards by the observation window 6 designed on electric furnace 1, detects insert site vibrational state.With
It is reference that finite element resonant frequency, which calculates result, finds the intrinsic frequency of testpieces.Shown in the following table of testing site.
Under record input frequency and state of temperature, the decaying course of normal pressure.Every 10 hours pause experimental observations and record
Surface abrasion situation between rubbing surface.Stop test when normal pressure decays to original 60%.
The present invention can also study wear-resisting insert surface roughness, hardness, material etc. influence rubbing surface performance factor with it is micro-
Relationship between dynamic abrasion.
Claims (8)
1. abrasion tester under a kind of hot environment, which is characterized in that including electric furnace (1) and vibration testing device (2), electric furnace
(1) to divide half structure, combination is enclosed in vibration testing device (2) outside, and vibration testing device (2) includes shake table (5), bracket
(3) and testpieces fixture (4).
2. abrasion tester under a kind of hot environment according to claim 1, it is characterised in that bracket (3) installation
On shake table (5), bracket (3) includes left and right bearing (7), upper mounting base (8), insert bracket (10) and the first insert
(11), mounting base (8) being fixedly installed in left and right bearing (7), insert bracket (10) is fixedly mounted on mounting base (8),
First insert (11) is connect with insert bracket (10).Wherein, above-mentioned bracket (3) is mounted on shake table (5) by bolt, left and right
Installation is bolted in bearing (7), upper mounting base (8), insert bracket (10).In addition, the first insert (11) and insert branch
Frame (10) is fixedly connected by soldering.
3. abrasion tester under a kind of hot environment according to claim 2, it is characterised in that the testpieces fixture
(4) be mounted in the vibration end of shake table (5), testpieces fixture (4) include fixture base (16), testpieces mounting rack (18),
Testpieces compact heap (17), testpieces (12) and the second insert (13), wherein fixture base (16) is mounted on the vibration of shake table (5)
On moved end, testpieces mounting rack (18) is located at fixture base (16) top, and testpieces compact heap (17) is bolted test
Part (12) is simultaneously located on testpieces mounting rack (18), and testpieces (12) is connect with the second insert (20).
4. abrasion tester under a kind of hot environment according to claim 3, it is characterised in that the fixture base
It (16) include front and back closure plate (15) and dovetail groove, testpieces mounting rack (18) further includes adjusting nut (14) and locking nut
(13), dovetail groove is fixed by front and back closure plate (15), and testpieces mounting rack (18) is mounted on dovetail groove, and passes through adjusting nut
(14) and locking nut (13) is mobile and fixed in dovetail groove.
5. abrasion tester under a kind of hot environment according to claim 4, it is characterised in that first insert
(11) and the friction face contact of the second insert (20).
6. abrasion tester under a kind of hot environment according to claim 5, it is characterised in that the testpieces (12)
Length is 90 to 100mm, and width 13 arrives 15mm, and thickness 2 arrives 4mm.
7. abrasion tester under a kind of hot environment according to claim 1, it is characterised in that above the electric furnace (1)
Corresponding first insert (11) and the position of the second insert (20) are equipped with right-angle view window (6).
8. abrasion tester under a kind of hot environment according to claim 1, it is characterised in that the right-angle view window
(6) it is made of quartz glass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910746437.2A CN110530750B (en) | 2019-08-13 | 2019-08-13 | Wear tester under high temperature environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910746437.2A CN110530750B (en) | 2019-08-13 | 2019-08-13 | Wear tester under high temperature environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110530750A true CN110530750A (en) | 2019-12-03 |
| CN110530750B CN110530750B (en) | 2022-10-21 |
Family
ID=68663136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910746437.2A Active CN110530750B (en) | 2019-08-13 | 2019-08-13 | Wear tester under high temperature environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110530750B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02297037A (en) * | 1989-05-12 | 1990-12-07 | Hitachi Ltd | Method and device for measuring vibration of blade |
| JP2008261884A (en) * | 2002-02-21 | 2008-10-30 | Yazaki Corp | Fretting corrosion testing device |
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| CN101419114A (en) * | 2007-10-24 | 2009-04-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for measuring fatigue test maximum stress of single-journal vane |
| CN201697772U (en) * | 2010-06-29 | 2011-01-05 | 长沙理工大学 | Experimental system for damping dynamic response of shrouded blades |
| CN202255880U (en) * | 2011-10-24 | 2012-05-30 | 三一电气有限责任公司 | Simulation test stand for variable-pitch systems |
| CN202734530U (en) * | 2012-06-28 | 2013-02-13 | 武汉市汉泰斯特科技有限公司 | Openable cylindrical high-power and high-temperature electric furnace for laboratory |
| JP2015072190A (en) * | 2013-10-03 | 2015-04-16 | 株式会社アドヴィックス | Shear characteristic measuring apparatus |
| CN104748928A (en) * | 2013-12-30 | 2015-07-01 | 天津航天瑞莱科技有限公司 | Vibratory fatigue testing method of aviation-engine blades based on electrodynamics vibration generator |
| CN105387719A (en) * | 2015-12-09 | 2016-03-09 | 贵州黎阳航空动力有限公司 | High-temperature electric resistance furnace used for fretting wear tests |
| CN105547882A (en) * | 2015-12-09 | 2016-05-04 | 贵州黎阳航空动力有限公司 | High-temperature micro-sliding-wear test system |
| CN108871991A (en) * | 2018-08-17 | 2018-11-23 | 西南交通大学 | A kind of gravitational load type fretting wear testing equipment that can simulate hot environment |
-
2019
- 2019-08-13 CN CN201910746437.2A patent/CN110530750B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02297037A (en) * | 1989-05-12 | 1990-12-07 | Hitachi Ltd | Method and device for measuring vibration of blade |
| JP2008261884A (en) * | 2002-02-21 | 2008-10-30 | Yazaki Corp | Fretting corrosion testing device |
| CN101419114A (en) * | 2007-10-24 | 2009-04-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for measuring fatigue test maximum stress of single-journal vane |
| CN101308057A (en) * | 2008-06-06 | 2008-11-19 | 北京航空航天大学 | Vibration damping test device possessing dry damping structure vane |
| CN201697772U (en) * | 2010-06-29 | 2011-01-05 | 长沙理工大学 | Experimental system for damping dynamic response of shrouded blades |
| CN202255880U (en) * | 2011-10-24 | 2012-05-30 | 三一电气有限责任公司 | Simulation test stand for variable-pitch systems |
| CN202734530U (en) * | 2012-06-28 | 2013-02-13 | 武汉市汉泰斯特科技有限公司 | Openable cylindrical high-power and high-temperature electric furnace for laboratory |
| JP2015072190A (en) * | 2013-10-03 | 2015-04-16 | 株式会社アドヴィックス | Shear characteristic measuring apparatus |
| CN104748928A (en) * | 2013-12-30 | 2015-07-01 | 天津航天瑞莱科技有限公司 | Vibratory fatigue testing method of aviation-engine blades based on electrodynamics vibration generator |
| CN105387719A (en) * | 2015-12-09 | 2016-03-09 | 贵州黎阳航空动力有限公司 | High-temperature electric resistance furnace used for fretting wear tests |
| CN105547882A (en) * | 2015-12-09 | 2016-05-04 | 贵州黎阳航空动力有限公司 | High-temperature micro-sliding-wear test system |
| CN108871991A (en) * | 2018-08-17 | 2018-11-23 | 西南交通大学 | A kind of gravitational load type fretting wear testing equipment that can simulate hot environment |
Non-Patent Citations (2)
| Title |
|---|
| 关桥: "《关桥论著选编》", 31 October 2002 * |
| 陈璐璐等: "带干摩擦阻尼结构叶片振动响应试验", 《航空动力学报》 * |
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| Publication number | Publication date |
|---|---|
| CN110530750B (en) | 2022-10-21 |
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