CN108414563B - The clamping device that thermal effect for ceramic matric composite part is tested - Google Patents
The clamping device that thermal effect for ceramic matric composite part is tested Download PDFInfo
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- CN108414563B CN108414563B CN201810046825.5A CN201810046825A CN108414563B CN 108414563 B CN108414563 B CN 108414563B CN 201810046825 A CN201810046825 A CN 201810046825A CN 108414563 B CN108414563 B CN 108414563B
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- clamping device
- heat radiation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
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- Life Sciences & Earth Sciences (AREA)
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- General Health & Medical Sciences (AREA)
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
This application discloses a kind of clamping devices that the thermal effect for ceramic matric composite part is tested, including inverted T shaped fixing component；For positioning the first positioning component of the ceramic matric composite part；And the second positioning component of at least one heat radiation part for positioning the ceramic matric composite part, wherein, first positioning component and second positioning component are arranged so that the ceramic matric composite part and the contactless parallel interval of at least one described heat radiation part are arranged.Pass through the clamping device of the application, ceramic matric composite part and its heat radiation part can be not only positioned simultaneously, heat radiation part can also be realized to the indirect heating of ceramic matric composite part, so as to carry out thermal effect test to ceramic matric composite part using high-frequency induction furnace method, the accurate control in temperature field is realized.
Description
Technical field
This application involves a kind of clamping devices, specifically but not exclusively, are related to a kind of for ceramic matric composite
(CMC) clamping device of the thermal effect test of part.
Background technique
Ceramic material has many advantages, such as high temperature resistant, density are low, corrosion-resistant, hardness is high.But its brittleness is to restrict
The key factor that ceramic material structure promotes and applies.Researcher carried out numerous studies to ceramic toughening method.
Method for toughening common at present includes short fiber reinforced (whisker reinforcement), stratiform toughening and continuous fiber toughening.Common toughening
Fiber includes glass fibre, high modulus carbon fiber, silicon carbide fibre, alumina fibre etc..The CMC formed by toughening has
Higher reliability, it is not easy to brittle failure phenomenon occur.
In aero-engine, the application prospect of CMC is very extensive, can on a variety of hot end stator parts, such as
Burner inner liner, turbine guide vane, turbine outer ring, jet pipe etc..However, applying CMC in aero-engine, it is necessary to its into
Row further investigation.Specifically, it according to the characteristic of conventional material, needs to be CMC a series of basic research, for example, it is desired to
Mechanical characteristic and the failure mechanism etc. for carrying out a large amount of repetitive tests further to study CMC, for example including CMC turbine guide vane heat
The thermal effect of fatigue test is tested.
Currently, commonly heating the method for CMC turbine guide vane in test includes high temperature box type resistance furnace heating and flame
Heating, but both heating means are all unable to accurately control the temperature field of CMC turbine guide vane.Although electromagnetic induction heating method energy
Enough precise control of temperature fields, but it is only applicable to as conductive material heating, and can not directly to nonconducting CMC turbine guide vane into
Row heating, therefore electromagnetic induction heating method is used, it must just be realized using heat radiation part and the indirect of CMC turbine guide vane is added
Heat.
In existing test, the clamping device of the thermal fatigue test of CMC turbine guide vane be usually be directed to flame heating or
Electric furnace heating is only used for positioning CMC turbine guide vane, and can not position CMC turbine guide vane and heat radiation part simultaneously, realizes heat
Indirect heating of the radiation component to CMC turbine guide vane.
Summary of the invention
In order to solve deficiency existing for above-mentioned prior art, the present invention provides a kind of for ceramic matric composite part
The clamping device of thermal effect test, can not only position ceramic matric composite part and its heat radiation part simultaneously, can also realize heat
Radiation component to the indirect heating of ceramic matric composite part, so as to using high-frequency induction furnace method to ceramic base composite wood
Materials and parts carry out thermal effect test, realize the accurate control in temperature field.
According to an aspect of the present invention, a kind of clamping device that the thermal effect for ceramic matric composite part is tested is provided,
The ceramic matric composite part have fixing end and with the continuous thermal effect test section of the fixing end, wherein the clamping device
Include:
There is the inverted T shaped fixing component of wing plate and web, be provided on the web of the inverted T shaped fixing component for inciting somebody to action
The clamping device is fixed on the fixation hole of testing stand；
For positioning the first positioning component of the ceramic matric composite part, one end of first positioning component with
The inverted T shaped fixing component connection, the other end are connect with the fixing end of the ceramic matric composite part；And
For position the ceramic matric composite part at least one heat radiation part the second positioning component, it is described extremely
A few heat radiation part have fixing end and with the continuous heat radiation section of the fixing end, one end of second positioning component and institute
Inverted T shaped fixing component connection is stated, the other end is connect with the fixing end of at least one heat radiation part,
Wherein, first positioning component and second positioning component are arranged so that the ceramic matric composite part
It is arranged with the contactless parallel interval of at least one described heat radiation part." contactless " described herein refers to that ceramic base is compound
Material pieces do not contact on the whole with heat radiation part, also do not need between the fixing end of the two using any escapement.
In some embodiments, first positioning component may include a pair of of Z-type component, each Z-type component
Upper flange is connect with the lower end surface of the inverted T shaped fixing component, and the fixing end of lower wing plate and the ceramic matric composite part is closed
Connection, wherein the relative distance between the pair of Z-type component is configured to position the ceramic matric composite on axial X
The fixing end of part.
In some embodiments, it can be set on the lower wing plate of each Z-type component and positioned the pottery on circumferential Y
The stop device of the fixing end of porcelain based composites part.
In some embodiments, the stop device may include the slot for being set to the lower wing plate of each Z-type component
Hole and the block that can be slided in the slot.
In some embodiments, the lower wing plate of each Z-type component can be arc panel, with ceramic matric composite
The arc of the construction section of part cooperates.
In some embodiments, the lower wing plate of each Z-type component can be surface plate.
In some embodiments, second positioning component may include at least one L-type side plate, it is described at least one
L-type side plate one end is connected to the lower end surface of the inverted T shaped fixing component, the upper plate of at least one L-type side plate by auricle
And/or waist-shaped hole can be set in lower plate.It is provided with waist-shaped hole on the upper plate and/or lower plate of L-type side plate, can not needed
In the case where redesigning, process and assembling clamping device, facilitate the thermal effect test section for adjusting ceramic matric composite part and heat
The relative altitude and/or relative distance of the heat radiation section of radiation component.
In some embodiments, first positioning component can also include being set to the inverted T shaped fixing component
The screw thread top tight pieces of at least one threaded hole and the cooperation of at least one described threaded hole, to position the ceramic base on radial Z
The fixing end of composite material element.In some embodiments, first positioning component can also include being placed in the screw thread top
Cushion block between tight part and the ceramic matric composite part, to prevent screw thread top tight pieces from directly applying to ceramic matric composite part
Pressure causes it impaired.
In some embodiments, the cushion block can be arc-shaped pad block, with the installation end with ceramic matric composite part
Arc cooperation.
In some embodiments, the cushion block can be flat mat.
In some embodiments, the upper flange and bottom wing of the wing plate of the inverted T shaped fixing component, each Z-type component
The vertical projection of plate can be parallelogram, be cooperated with the structure of the construction section with ceramic matric composite part.
In some embodiments, at least one described heat radiation part can have continuously supports with the heat radiation section
End, the clamping device may include at least one support, and the support is connect with the support end of the heat radiation part.
Detailed description of the invention
It, below will be to required in embodiment description in order to illustrate more clearly of the technical solution in the application embodiment
Attached drawing to be used is briefly described, it should be apparent that, the accompanying drawings in the following description is only some embodiment party of the application
Formula without creative efforts, can also obtain according to these attached drawings for those of ordinary skill in the art
Obtain other attached drawings.
Fig. 1 is the partial structural diagram of CMC turbine guide vane.
Fig. 2 is the assembling schematic diagram of clamping device according to the present invention and heat radiation part, CMC turbine guide vane.
Fig. 3 (a) and (b) are the structural schematic diagrams of heat radiation part shown in Fig. 2.
Fig. 4 is the structural schematic diagram of the inverted T shaped fixing component of clamping device according to the present invention.
Fig. 5 (a) to (c) is the structural schematic diagram of the Z-type component of clamping device according to the present invention.
Fig. 6 is the Z-type component of clamping device according to the present invention and the assembling schematic diagram of CMC turbine guide vane.
Fig. 7 is the vertical projection figure of Fig. 6.
Fig. 8 is the vertical projection figure of the inverted T shaped fixing component of clamping device according to the present invention.
Fig. 9 is the assembling schematic diagram of clamping device according to the present invention Yu CMC turbine guide vane.
Figure 10 is the assembling schematic diagram of clamping device according to the present invention Yu heat radiation part.
Specific embodiment
Clear, complete description is carried out to presently filed embodiment below in conjunction with attached drawing, it is clear that described embodiment party
Formula is merely possible to illustrate, and is not intended to limit the application.Generally, clamping device of the present invention is indicated with 10.
In the following description, using the CMC turbine guide vane 20 of aero-engine as the example of ceramic matric composite part.
It will be understood by those skilled in the art that embodiments of the present invention can be adapted for any ceramics similar to turbine guide vane etc
Based composites part.
As shown in Figure 1, CMC turbine guide vane 20 has supramarginal plate 201 and blade 202, wherein supramarginal plate 201 is fixing end,
Blade 202 is thermal effect test section.The upper end (one end far from blade 202) of supramarginal plate 201 has convex to two sides respectively along axial X
Construction section 2011,2011 ' out.It should be understood that the turbine in axial direction X, circumferential direction Y and radial direction Z described herein and engine
The orientation of guide vane is consistent.
As shown in Fig. 2 and Fig. 3 (a)-(b), CMC turbine guide vane 20 can be respectively arranged with hot spoke in its 202 two sides of blade
Penetrate part 30,30 ', wherein heat radiation part 30 is blade back heat radiation part, and heat radiation part 30 ' is leaf basin heat radiation part.Heat radiation part
30,30 ' have heat radiation section 302,302 '.Particularly, heat radiation section 302,302 ' be irregular curved slab, is divided into inside
(close to the side of blade) and outside (side far from blade).The curve form of inside and the surface shape of blade are corresponding, outside
The curved surface of side is formed by the substantially uniform thickening of curved surface of inside, that is, the basic uniform thickness everywhere of heat radiation section 302,302 '.Particularly,
The thickness of heat radiation section 302,302 ' can be 1-3mm, preferably 2mm.Particularly, heat radiation section 302,302 ' height are answered
It is consistent with 202 height of blade as far as possible.One end of heat radiation section 302,302 ' is provided with fixing end, and support has can be set in the other end
End.In this example, heat radiation section 302,302 ' both ends are welded with auricle 301,303 with holes；301 ', 303 '.It should be understood that can
The shape and quantity of heat radiation part to be arranged according to the structure of ceramic matric composite part.
Clamping device 10 may include inverted T shaped fixing component 101, the Z-type component 102 for positioning CMC turbine guide vane 20,
102 ' and be used for positioning heat radiation component 30,30 ' 103,103 ' (not shown) of L-type side plate.In this example, clamping device 10 is gone back
May include the support 104,104 ' being connect with the support end of heat radiation part 30,30 ', support 104,104 ' respectively with heat radiation part
30,30 ' auricle with holes 303,303 ' connects, in order to which entire assembly parts are placed on testing stand.
Particularly, heat radiation part 30,30 ' are arranged with the contactless parallel interval of CMC turbine guide vane 20.
In this embodiment, Z-type component 102,102 ' can be bolted with inverted T shaped fixing component 101 by through-hole.
For example, can be bolted using 4 symmetrical through-holes (such as φ 4.5mm).
As shown in figure 4, inverted T shaped fixing component 101 includes wing plate 1011,1011 ' and web 1012.Wherein, web 1012
On mounting hole for clamping device 10 to be fixed on to thermal effect testing stand can be set, the quantity of the mounting hole can be according to examination
The structure for testing platform is configured.Inverted T shaped fixing component 101 can also include at least one auricle with holes, and heat radiation part is connected
It is connected to inverted T shaped fixing component 101.In this example, 1013,1013 ' (not shown) of auricle with holes is respectively fixedly connected with to inverted T shaped
At the intermediate lateral margin of the wing plate 1011,1011 ' of fixing component 101.Particularly, auricle 1013,1013 ' with holes can be soldered to down
T-type fixing component 101.
As shown in Fig. 5 (a)-(b), Z-type component 102,102 ' have upper flange 1021,1021 ', web 1022,1022 ' and
Lower wing plate 1023,1023 '.Plane is connected to the wing plate of inverted T shaped fixing component 101 respectively for the upper surface of upper flange 1021,1021 '
1011,1011 ' lower end surface, the construction section with the supramarginal plate 201 of CMC turbine guide vane 20 respectively of lower wing plate 1023,1023 '
2011,2011 ' associations.
As shown in Fig. 5 (c), the construction section 2011 of the supramarginal plate 201 of the lower wing plate and CMC turbine guide vane 20 of Z-type component,
2011 ' contact surface is the arc of radius R, the arc with the construction section 2011,2011 ' of the supramarginal plate 201 of CMC turbine guide vane 20
Shape adaptation.It should be understood that as needed, the contact surface of the lower wing plate and ceramic matric composite part of each Z-type component may be
Plane or other curved surfaces.
Particularly, Z-type component 102, the relative position between 102 ' may be configured to position CMC turbine on axial X
Guide vane 20.As shown in fig. 6, can be positioning side with side S1, S1 of the lower wing plate 1023,1023 ' of Z-type component 102,102 ' ',
Limitation CMC turbine guide vane 20 moves on axial X.In some embodiments, when the axial length of construction section 2011,2011 '
Greater than lower wing plate 1023,1023 ' axial length when, can be with the vertical of the web 1022,1022 ' of Z-type component 102,102 '
Face S2, S2 ' it is positioning surface, limitation CMC turbine guide vane 20 moves on axial X.In some embodiments, Z-type component 102,
Positioning step can be set on 102 ' lower wing plate 1023,1023 ', moved with limiting CMC turbine guide vane 20 on axial X.
As described in Fig. 7-8, wing plate, the upper flange of Z-type component and the vertical projection of lower wing plate of inverted T shaped fixing component 101
It can be parallelogram, be cooperated with the structure of the construction section of the supramarginal plate with CMC turbine guide vane 20.In this example, this is flat
The acute angle of the adjacent edge of row quadrangle is 60 °
Particularly, Z-type component 102 can be set on 102 ' lower wing plate 1023,1023 ' and prevent CMC turbine guide vane 20
The stop device that is moved on circumferential Y of supramarginal plate 201.The stop device may include being set to Z-type component 102,102 '
The slot of lower wing plate 1023,1023 ' and the block that can be slided in the slot.In some embodiments, which can
Think waist-shaped hole, circumferential lengths are greater than the circumferential width of the construction section of the supramarginal plate of CMC turbine guide vane 20.In this example
(as shown in Figure 9), the slot can be open slot, and circumferential lengths are greater than the circumferential width of construction section.In some embodiment party
In formula, the construction section of the supramarginal plate 201 of CMC turbine guide vane 20 can be positioned with side using the step of slot end design, another
Side is positioned using the block that can be slided in the slot.In some embodiments, the peace of the supramarginal plate of CMC turbine guide vane 20
Dress section can utilize block to position with two sides.
Particularly, which can be backstop bolt 105.
As shown in figure 9, clamping device 10 can also include the wing plate 1011,1011 ' for being set to inverted T shaped fixing component 101
On threaded hole, and with the threaded hole cooperation screw thread top tight pieces 106.The screw thread top tight pieces 106 act on CMC turbine guide vane
The upper surface of the construction section 2011,2011 ' of 20 supramarginal plate, to position CMC turbine guide vane 20 on radial Z.
In this example, between the upper surface of the construction section of the supramarginal plate of the screw thread top tight pieces 106 and CMC turbine guide vane 20
Cushion block 107 can be set, to prevent screw thread top tight pieces 106 from directly causing supramarginal plate impaired supramarginal plate pressure.Particularly, should
The contact surface of the construction section of cushion block 107 and supramarginal plate is arc, the arc with the construction section of the supramarginal plate of CMC turbine guide vane 20
Adaptation.It should be understood that as needed, the contact surface of cushion block 107 and ceramic matric composite part may be plane or other songs
Face.Preferably, the cushion block 107 is made of aluminum.
Particularly, the height of Z-type component 102,102 ' web 1022,1022 ' can be unequal.
As shown in Figure 10, L-type side plate 103,103 ' (not shown) upper plate inverted T shaped fixation can be connected to by waist-shaped hole
1013, the 1013 ' (not shown) of auricle with holes of component 101 makes itself and leaf can adjust the height of heat radiation section 302,302 '
Body 202 is in same level height.The lower plate of L-type side plate 103,103 ' can be connected to heat radiation part 30,30 ' by waist-shaped hole
Auricle with holes 301,301 ', the distance between the blade of heat radiation section 302,302 ' Yu CMC turbine guide vane 20 can be adjusted,
To control the heating speed of thermal effect test.
In some embodiments, heat radiation part 30,30 ' can be made of high-temperature alloy steel, such as GH4169.
In some embodiments, inverted T shaped fixing component 101, Z-type component 102,102 ' and support 104,104 ' can be by
Stainless steel is made, such as 304 stainless steels.
What is applied above is only some embodiments of the application.For those of ordinary skill in the art, not
Under the premise of being detached from the application concept, several variations and modifications can also be made, these belong to the protection model of the application
It encloses.
Claims (10)
1. a kind of clamping device (10) that the thermal effect for ceramic matric composite part is tested, the ceramic matric composite part tool
Have fixing end and with the continuous thermal effect test section of the fixing end, which is characterized in that the clamping device (10) includes:
Inverted T shaped fixing component with wing plate and web is provided on the web of the inverted T shaped fixing component for will be described
Clamping device (10) is fixed on the fixation hole of testing stand；
For positioning the first positioning component of the ceramic matric composite part, one end of first positioning component with it is described
Inverted T shaped fixing component connection, the other end are connect with the fixing end of the ceramic matric composite part；And
For position the ceramic matric composite part at least one heat radiation part the second positioning component, described at least one
A heat radiation part have fixing end and with the continuous heat radiation section of the fixing end, one end of second positioning component and it is described fall
The connection of T-type fixing component, the other end are connect with the fixing end of at least one heat radiation part,
Wherein, first positioning component and second positioning component are arranged so that the ceramic matric composite part and institute
State the contactless parallel interval setting of at least one heat radiation part.
2. clamping device (10) according to claim 1, which is characterized in that first positioning component includes a pair of of Z-type
The upper flange of component, each Z-type component is connect with the lower end surface of the inverted T shaped fixing component, lower wing plate and the ceramic base
The fixing end of composite material element is associated with,
Wherein, the relative distance between the pair of Z-type component is configured to position the ceramic base composite wood on axial direction (X)
The fixing end of materials and parts.
3. clamping device (10) according to claim 2, which is characterized in that be arranged on the lower wing plate of each Z-type component
There is the stop device for the fixing end that the ceramic matric composite part is positioned on circumferential direction (Y).
4. clamping device (10) according to claim 3, which is characterized in that the stop device is each described including being set to
The slot of the lower wing plate of Z-type component and the block that can be slided in the slot.
5. clamping device (10) according to claim 4, which is characterized in that shown slot is open slot, and the block is
Backstop bolt.
6. clamping device (10) according to claim 5, which is characterized in that the lower wing plate of each Z-type component is arc
Plate.
7. clamping device (10) according to claim 6, which is characterized in that second positioning component includes at least one
L-type side plate, at least one described L-type side plate one end are connected to the lower end surface of the inverted T shaped fixing component by auricle, it is described extremely
Waist-shaped hole is provided on the upper plate and/or lower plate of a few L-type side plate.
8. clamping device (10) according to claim 7, which is characterized in that first positioning component further includes being set to
At least one threaded hole of the inverted T shaped fixing component, at least one described threaded hole cooperation screw thread top tight pieces and set
Cushion block between the screw thread top tight pieces and the ceramic matric composite part, the cushion block are arc cushion block.
9. clamping device (10) according to claim 8, which is characterized in that the wing plate of the inverted T shaped fixing component, each institute
The vertical projection of the upper flange and lower wing plate of stating Z-type component is parallelogram.
10. clamping device described in one of -9 (10) according to claim 1, which is characterized in that at least one described heat radiation part
With with the continuous support end of heat radiation section, the clamping device (10) includes at least one support, the support and institute
State the support end connection of heat radiation part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810046825.5A CN108414563B (en) | 2018-01-18 | 2018-01-18 | The clamping device that thermal effect for ceramic matric composite part is tested |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810046825.5A CN108414563B (en) | 2018-01-18 | 2018-01-18 | The clamping device that thermal effect for ceramic matric composite part is tested |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108414563A CN108414563A (en) | 2018-08-17 |
| CN108414563B true CN108414563B (en) | 2019-03-22 |
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| CN201810046825.5A Active CN108414563B (en) | 2018-01-18 | 2018-01-18 | The clamping device that thermal effect for ceramic matric composite part is tested |
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Families Citing this family (1)
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| CN109186908B (en) * | 2018-08-24 | 2020-10-13 | 北京航空航天大学 | Cooling clamping device for high-temperature vibration test of turbine guide vane |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7722317B2 (en) * | 2007-01-25 | 2010-05-25 | Siemens Energy, Inc. | CMC to metal attachment mechanism |
| CN102061372B (en) * | 2010-11-04 | 2012-06-13 | 西安航空动力股份有限公司 | Quartz ceramic heating tool clamp and manufacturing method thereof |
| US20140248146A1 (en) * | 2012-08-31 | 2014-09-04 | United Technologies Corporation | Attachment apparatus for ceramic matrix composite materials |
| CN104807743A (en) * | 2015-04-21 | 2015-07-29 | 北京航空航天大学 | Heating method for ceramic-based composite material |
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