CN207227293U - A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture - Google Patents
A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture Download PDFInfo
- Publication number
- CN207227293U CN207227293U CN201720703821.0U CN201720703821U CN207227293U CN 207227293 U CN207227293 U CN 207227293U CN 201720703821 U CN201720703821 U CN 201720703821U CN 207227293 U CN207227293 U CN 207227293U
- Authority
- CN
- China
- Prior art keywords
- module
- aerofoil profile
- listrium
- blade
- leaf basin
- Prior art date
- 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.)
- Active
Links
Abstract
The utility model discloses a kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture, listrium module（4）Top be provided with and the big listrium of blade precast body（3）Matched cavity A（8）, small listrium module（5）Bottom be provided with and small listrium（2）Matched cavity B（11）, blade back aerofoil profile module（6）Rear side be provided with and blade back aerofoil profile（21）Matched curved surface（12）, leaf basin aerofoil profile module（7）Front side be provided with and leaf basin aerofoil profile（22）Matched protrusion（14）.The beneficial effects of the utility model are：Ensure finished product front side of vane without or the processing of few surplus, fast assembling-disassembling and assembling, the near-net-shape for effectively realizing ceramic matrix composite turbine stator blade, manufacture cost it is low.
Description
Technical field
It the utility model is related to and belong to technical field of aircraft engine part manufacture, particularly a kind of aero-engine pottery
Porcelain based composites turbine nozzle vane near-net-shape fixture.
Background technology
One of the part of ceramic matrix composite turbine stator blade as aero-engine most critical, since turbine is led
To device blade working environment very severe, warm highest is held, strong heat erosion is born, bears thermal shock most serious, and ceramic base
Composite material most possibly substitutes nickel-base high-temperature because of the excellent performance such as density is small, specific strength is high, specific stiffness is high, heat-resisting quantity is good
The turbine nozzle vane high-temperature material that alloy uses at a higher temperature is ceramic matric composite.Ceramic matric composite one
As refer to carbon fiber reinforced carbon matrix（C/C）Composite material, carbon fibre reinforced silicon carbide ceramic base（C/SiC）Composite material, carborundum
Silicon carbide fiber reinforced ceramic base（SiC/SiC）Composite material, is a kind of superhigh temperature composite material, and operating temperature is up to 1650
℃。
At present, it is blade precast body braiding → chemistry gas that ceramic matrix composite turbine stator blade, which is typically prepared process,
Mutually ooze product（Chemical vapor infiltration, CVI）Boundary layer → matrix densification（Using CVI and PIP technologies）→
Mechanical processing → prepared by coating → is inspected for acceptance.High performance ceramic base composite turbine guider with three-dimensional aerofoil profile blade
Blade, it is necessary to using 3 D weaving（Such as 2.5D, three-dimensional four-way, three-dimensional five are to, orthogonal three-dimensional）Method braiding guide vane is pre-
Body processed, the preparation of blade especially its working face require near-net-shape（Blade does not allow or allows machinery on a small quantity i.e. in preparation process
Processing）.But it is relatively soft by the blade precast body of fibrage, and can not possibly reach blade three-dimensional aerofoil profile etc. by the blade of braiding
Design size.In the preparation process such as blade precast body CVI deposited interfacial layers, matrix densification initial stage, because will not
Blade precast body carries out frock, and the geomery of ceramic matrix composite vane is difficult to guarantee, it may appear that warpage, distortion, protrusion etc.
Defect, causes ceramic matrix composite turbine stator blade to prepare failure.Wherein, the structure of blade precast body such as Fig. 1 and 2 institutes
Show, blade precast body includes body（1）, small listrium（2）With big listrium（3）Composition, small listrium（2）It is fixed on body（1）Top,
Small listrium（2）It is fixed on body（1）Bottom, body（1）Front portion be blade back aerofoil profile（21）, rear leaf basin aerofoil profile（22）.
Utility model content
The purpose of the utility model is to overcome the shortcomings that the prior art, there is provided one kind ensure finished product front side of vane without or
Few surplus processing, fast assembling-disassembling and assembling, the near-net-shape for effectively realizing ceramic matrix composite turbine stator blade, manufacture
The low aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture of cost.
The purpose of this utility model is achieved through the following technical solutions：A kind of aero-engine ceramic matric composite whirlpool
Stator blade near-net-shape fixture is taken turns, it includes big listrium module, small listrium module, blade back aerofoil profile module and leaf basin aerofoil profile
Module, be provided with the top of the big listrium module with the matched cavity A of the big listrium of blade precast body, in big listrium module
The blade back locating piece and leaf basin locating piece for being located at cavity A left and right sides respectively are additionally provided with, blade back locating piece is located at leaf basin locating piece
Front side, the bottom of the small listrium module is provided with and the matched cavity B of small listrium；The blade back aerofoil profile module
Rear side is provided with offers the first location hole, blade back aerofoil profile with the matched curved surface of blade back aerofoil profile, the bottom of blade back aerofoil profile module
Module is positioned in big listrium module and the first location hole is engaged with blade back locating piece；The front side of the leaf basin aerofoil profile module
It is provided with and offers the second location hole, leaf basin aerofoil profile module with the matched protrusion of leaf basin aerofoil profile, the bottom of leaf basin aerofoil profile module
It is positioned in big listrium module and the second location hole is engaged with leaf basin locating piece；The leaf basin aerofoil profile module and blade back aerofoil profile
The left and right sides of module is fixedly provided with installing plate, and leaf basin aerofoil profile module and blade back aerofoil profile module may be contained within big listrium module and small
Between listrium module, locking short screw is provided between the installing plate of leaf basin aerofoil profile module and the installing plate of blade back aerofoil profile module,
Locking long spiro nail, and blade back aerofoil profile module, big listrium are provided between leaf basin aerofoil profile module, big listrium module and small listrium module
Locking long spiro nail is provided between module and small listrium module；The big listrium module is distributed with multiple connections in appearance
The aperture of cavity A, the apertures of multiple connection cavity B is distributed with the outer surface of small listrium module, blade back aerofoil profile module is just
EDS maps have multiple apertures through curved surface, are provided with behind leaf basin aerofoil profile module multiple through raised aperture.
Two mounting plates structures in the aerofoil profile module are identical.
Locking nut is threaded with the locking short screw and locking long spiro nail.
The spacing between spacing, longitudinally adjacent two apertures between laterally adjacent two apertures is 7 ~ 8mm.
A diameter of 2~3mm of the aperture.
The utility model has the following advantages：（1）The utility model is designed by using high-temperature alloy or graphite material
Four module, then coordinated using the screw tightened with nut and exerted a force, it is fixed and compress, be compacted blade precast body, it is near for blade
Dead size shaping provides advantage.（2）This fixture ensure that front side of vane without or the processing of few surplus, avoid destruction leaf
The three-dimensional fiber braiding structure of piece and avoid and reduce Blade Properties index, improve blade and prepare quality and production efficiency.
Brief description of the drawings
Fig. 1 is the structure diagram of blade precast body；
Fig. 2 is the right view of Fig. 1；
Fig. 3 is the structure diagram of the utility model；
Fig. 4 removes the structure diagram after blade back aerofoil profile module, leaf basin aerofoil profile module for the utility model；
Fig. 5 removes the structure diagram after big listrium module, small listrium module for the utility model；
Fig. 6 is the structure diagram of big listrium module；
Fig. 7 is the structure diagram of small listrium module；
Fig. 8 is the structure diagram of blade back aerofoil profile module；
Fig. 9 is the bottom view of Fig. 8；
Figure 10 is the structure diagram of leaf basin aerofoil profile module；
The bottom view of Figure 11 Figure 10；
In figure, 1- bodies, the small listriums of 2-, the big listriums of 3-, the big listrium modules of 4-, the small listrium modules of 5-, 6- blade back aerofoil profile moulds
Block, 7- leaf basin aerofoil profile modules, 8- cavitys A, 9- blade back locating piece, 10- leaf basin locating pieces, 11- cavitys B, 12- curved surface, 13- first
Location hole, 14- is raised, the second location holes of 15-, 16- installing plates, 17- locking short screws, 18- locking long spiro nails, 19- apertures,
20- locking nuts, 21- blade back aerofoil profiles, 22- leaf basin aerofoil profiles.
Embodiment
The utility model is further described below in conjunction with the accompanying drawings, the scope of protection of the utility model be not limited to
It is lower described：
As shown in Fig. 3 ~ 11, a kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape folder
Tool, it includes big listrium module 4, small listrium module 5, blade back aerofoil profile module 6 and leaf basin aerofoil profile module 7, the big listrium mould
The top of block 4 is provided with listrium 3 matched cavity A8 big with blade precast body, and position respectively is additionally provided with big listrium module 4
In the blade back locating piece 9 and leaf basin locating piece 10 of cavity A8 left and right sides, blade back locating piece 9 is located at the front side of leaf basin locating piece 10,
The bottom of the small listrium module 5 is provided with and the matched cavity B11 of small listrium 2；After the blade back aerofoil profile module 6
Side is provided with curved surface 12 matched with blade back aerofoil profile 21, and the bottom of blade back aerofoil profile module 6 offers the first location hole 13, blade back
Aerofoil profile module 6 is positioned in big listrium module 4 and the first location hole 13 is engaged with blade back locating piece 9；The leaf basin aerofoil profile
The front side of module 7 be provided with leaf basin aerofoil profile 22 matched raised 14, the bottom of leaf basin aerofoil profile module 7 offers the second positioning
Hole 15, leaf basin aerofoil profile module 7 is positioned in big listrium module 4 and the second location hole 15 is engaged with leaf basin locating piece 10；It is described
Leaf basin aerofoil profile module 7 and the left and right sides of blade back aerofoil profile module 6 be fixedly provided with installing plate 16, leaf basin aerofoil profile module 7 and blade back
Aerofoil profile module 6 may be contained between big listrium module 4 and small listrium module 5, installing plate 16 and the blade back wing of leaf basin aerofoil profile module 7
Locking short screw 17, leaf basin aerofoil profile module 7, big listrium module 4 and small listrium module are provided between the installing plate 16 of pattern block 6
Locking long spiro nail 18 is provided between 5, locking nut 20 is threaded with locking short screw 17 and locking long spiro nail 18, and
Locking long spiro nail 18 is provided between blade back aerofoil profile module 6, big listrium module 4 and small listrium module 5；The big listrium module
4 apertures 19 for being distributed with multiple connection cavity A8 in appearance, are distributed with multiple connections on the outer surface of small listrium module 5
Multiple apertures 19 through curved surface 12, leaf basin aerofoil profile module 7 is distributed with the aperture 19 of cavity B11, the front of blade back aerofoil profile module 6
Behind be provided with it is multiple through protrusion 14 apertures 19.The main function of aperture：1st, CVI prepares boundary layer or matrix densification
During, there is provided passage makes reacting gas enter reactive deposition ceramic matrix on blade precast body；2nd, in PIP densifications, there is provided
Passage make reaction solution enter blade precast body on impregnated, then in Pintsch process, there is provided passage makes the nothing after reaction
Discharged with gas reactant from blade precast body.
Two 16 structures of installing plate in the aerofoil profile module are identical.Between laterally adjacent two apertures 19
Spacing between spacing, longitudinally adjacent two apertures 19 is 7 ~ 8mm；A diameter of 2~3mm of the aperture 19.
The preparation of aero-engine ceramic matrix composite turbine stator blade near-net-shape comprises the following steps：
S1, using special braider weave 3 D weaving turbine nozzle vane precast body, the structure of blade precast body is such as
Shown in Fig. 1 and 2.
Turbine nozzle vane precast body, is placed on progress high temperature pretreatment in vacuum high-temperature heat-treatment furnace, pre- place by S2
700 DEG C~2400 DEG C of the temperature of reason, time are protected for 1h~3h, using vacuum or inert gas, and pretreatment purpose is
Except blade precast body surface removing residual glue, improve blade precast body mechanical property；
S3, to turbine nozzle vane precast body CVI boundary layers, it specifically includes following steps：
S3（I）Blade precast body is positioned over frock in this fixture, specific frock process is：By small listrium module 5
Cavity B11 is engaged with the small listrium 2 of blade precast body, ensure blade precast body placing direction and both be smooth connection, no
The problem of being uneven can occur；The cavity A8 of big listrium module 4 is engaged with the big listrium 3 of blade precast body, ensures blade
Precast body placing direction and both be smooth connection, it is impossible to there is the problem of being uneven；Blade back locating piece 9 is assembled in big listrium
In module 4, blade back locating piece 9 is assembled in the first location hole 13 of blade back aerofoil profile module 6, to determine big listrium module 4, blade back
Relative position between aerofoil profile module 6 and blade precast body；Blade back aerofoil profile module 6, small listrium module 5, big listrium module 4 are led to
Locking long spiro nail 18 is crossed to be connected；Leaf basin locating piece 10 is assembled in big listrium module 4, leaf basin locating piece 10 is assembled to the leaf basin wing
In second location hole 15 of pattern block 7, to determine that small listrium module 5, big listrium module 4, leaf basin aerofoil profile module 7 and blade are prefabricated
Relative position between body；Leaf basin aerofoil profile module 7, small listrium module 5, big listrium module 4 are connected by locking long spiro nail 18；
Locking short screw 17 is used to be connected with locking nut 20 to fix blade back aerofoil profile module 6, leaf basin aerofoil profile module 7；Tighten locking length
Locking nut 20 on screw 18, to be compacted, compress blade precast body, realizes the Rapid tooling of blade precast body, so as to protect
The compact dimensions for having demonstrate,proved blade precast body reach Design Requirement Drawing；
S3（II）By step S（I）In is fitted into equipped with the fixture of blade precast body in CVI stoves, using technical parameter progress CVI
Prepared by boundary layer, boundary layer includes pyrolysis carbon boundary layer and BN boundary layers.CVI prepares pyrolysis carbon boundary layer and uses methane or propane
Prepare BN boundary layers as reacting gas, CVI with natural gas and use NH3Gas and BCl3Gas is as reacting gas, reacting gas
It is passed through through the aperture 19 on fixture in fixture, CVI preparation temperatures are 700 DEG C~1100 DEG C, the time is 0.5h~4h.
S4, due to preparing boundary layer using CVI after, blade precast body is still soft, unformed, need to be to turbine nozzle vane
The initial stage matrix densification of precast body.It specifically includes following steps：
S4（I）Processed blade precast body in step S3 is taken out and loaded in another fixture, frock mode and S3（I）
It is identical；
S4（II）Fixture combination body equipped with blade precast body is fitted into CVI stoves or PIP stoves, using technology of preparing parameter
Carry out ceramic matrix densification to prepare, ceramic matrix includes C and SiC.CVI prepares C matrix and uses methane or propane and natural gas
As reacting gas, CVI prepares SiC matrix and uses trichloromethyl silane（CH3SiCl3）、H2Gas and BCl3Gas is as reaction
Gas, CVI preparation temperatures are 700 DEG C~1100 DEG C, the time is 20h~100h.Precursor dipping pyrolysis（precursor
Impregnation pyrolysis, PIP）Prepare SiC matrix to be impregnated using Polycarbosilane and xylene solution, Ran Hou
Dried in baking oven, then Pintsch process is carried out in vacuum high-temperature treatment furnace（800 DEG C~1200 DEG C of cracking temperature, time
0.5h~3h）, this dipping, drying, cracking process are then subjected to iterative cycles totally 3 times~7 times；
S4（III）By step S4（2）In fixture taken out from CVI stoves or PIP stoves；
S4（IV）Blade precast body is taken out from fixture, the inverse process that process is frock process is taken out, is checked after taking-up
Whether blade precast body has been hardened and has shaped, and next process is sent into if being hardened and having shaped, if not being hardened and determining
Type then repeat step S4（II）；
The final matrix densification of S5, turbine nozzle vane precast body, are to make the prefabricated volume density of turbine nozzle vane
Reach final design requirement（It is required that density is 1.8g/cm3~2.6g/cm3）, its concrete operation step is：
S5（I）, blade precast body put to be fitted into CVI stoves or PIP stoves carry out final ceramic matrix densification and prepare, blade
The final ceramic matrix densification of precast body should be the supplement process of its initial stage matrix densification preparation, both reaction gases
The preparation conditions such as body, preparation parameter, preparation process are identical, and simply the former preparation time is longer, such as prepare C bases using CVI
Body or SiC matrix, its preparation time should be 200h~600h；Or as prepared SiC matrix using PIP, iterative cycles number should be 9
It is secondary~13 times.
S5（II）Blade precast body is taken out from CVI stoves or PIP stoves, the prefabricated volume density of turbine nozzle vane has been at this time
Up to finally density is required, complete matrix densification, is hardened and shapes completely, it has also become ceramic matrix composite vane hair
Base；
The mechanical processing of S6, ceramic matrix composite vane blank.Due to step S5（II）Middle ceramic matric composite leaf
The working face size of piece blank near-net-shape, but other non-working surface sizes must also be machined by design requirement.
S7. prepared by the coating of ceramic matrix composite vane.In order to improve the aero-engines such as high-temperature oxydation, high temperature corrosion
Military service performance under working environment, ceramic matrix composite vane such as must use chemical vapor deposition in its surface prepares coating
（Chemical vapor deposition, CVD）Method prepares SiC coatings：Blade is positioned in CVD stoves, using corresponding system
Standby technical parameter carries out CVD and prepares SiC coatings.CVD prepares SiC matrix and uses trichloromethyl silane（CH3SiCl3）、H2Gas is made
For reacting gas, gas enters through aperture 19, and CVD preparation temperatures are 900 DEG C~1200 DEG C, the time is 10h~60h；
The inspection and examination of S8, ceramic matrix composite turbine stator blade.After process made above, ceramic base
Composite turbine stator blade has completed all preparation process, must be checked and checked and accepted by blade design drawing requirement,
Pass through rear as qualified ceramic matrix composite turbine stator blade finished parts.
Since the top of big listrium module 4 is provided with listrium 3 matched cavity A8 big with blade precast body, small listrium mould
The bottom of block 5 is provided with to be provided with and blade back aerofoil profile 21 with the matched cavity B11 of small listrium 2, the rear side of blade back aerofoil profile module 6
Matched curved surface 12, the front side of leaf basin aerofoil profile module 7 be provided with leaf basin aerofoil profile 22 matched raised 14, carry out near net into
During type, ensure that front side of vane without or the processing of few surplus, avoid the three-dimensional fiber braiding structure for destroying blade and avoid
Blade Properties index is reduced, blade is improved and prepares quality and production efficiency.In addition, this fixture middle period basin aerofoil profile module 7 and leaf
Locked between backlimb pattern block 6 by locking short screw 17 with locking nut 20, and leaf basin aerofoil profile module 7, big listrium mould
Locked between block 4 and small listrium module 5 by locking long spiro nail 18 with locking nut 20, and blade back aerofoil profile module 6, big edge
Locked between plate module 4 and small listrium module 5 by locking long spiro nail 18 with locking nut 20, using the screw tightened with
Nut coordinates force, fixes and compresses, is compacted blade precast body, advantage is provided for blade near-net-shape, and
It is all very convenient in work assembly and disassembly, save and improve production efficiency.
Claims (5)
- A kind of 1. aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture, it is characterised in that：It Including big listrium module（4）, small listrium module（5）, blade back aerofoil profile module（6）With leaf basin aerofoil profile module（7）, the big listrium Module（4）Top be provided with and the big listrium of blade precast body（3）Matched cavity A（8）, big listrium module（4）On also set It is equipped with and is located at cavity A respectively（8）The blade back locating piece of left and right sides（9）With leaf basin locating piece（10）, blade back locating piece（9）Positioned at leaf Basin locating piece（10）Front side, the small listrium module（5）Bottom be provided with and small listrium（2）Matched cavity B （11）；The blade back aerofoil profile module（6）Rear side be provided with and blade back aerofoil profile（21）Matched curved surface（12）, blade back aerofoil profile Module（6）Bottom offer the first location hole（13）, blade back aerofoil profile module（6）It is positioned over big listrium module（4）It is upper and first Location hole（13）With blade back locating piece（9）It is engaged；The leaf basin aerofoil profile module（7）Front side be provided with and leaf basin aerofoil profile （22）Matched protrusion（14）, leaf basin aerofoil profile module（7）Bottom offer the second location hole（15）, leaf basin aerofoil profile module （7）It is positioned over big listrium module（4）Upper and the second location hole（15）With leaf basin locating piece（10）It is engaged；The leaf basin aerofoil profile Module（7）With blade back aerofoil profile module（6）Left and right sides be fixedly provided with installing plate（16）, leaf basin aerofoil profile module（7）With the blade back wing Pattern block（6）It may be contained within big listrium module（4）With small listrium module（5）Between, leaf basin aerofoil profile module（7）Installing plate（16） With blade back aerofoil profile module（6）Installing plate（16）Between be provided with locking short screw（17）, leaf basin aerofoil profile module（7）, big listrium Module（4）With small listrium module（5）Between be provided with locking long spiro nail（18）, and blade back aerofoil profile module（6）, big listrium module （4）With small listrium module（5）Between be provided with locking long spiro nail（18）；The big listrium module（4）Be distributed in appearance There are multiple connection cavity A（8）Aperture（19）, small listrium module（5）Outer surface on be distributed with multiple connection cavity B（11） Aperture（19）, blade back aerofoil profile module（6）Front be distributed with and multiple run through curved surface（12）Aperture（19）, leaf basin aerofoil profile module （7）Behind be provided with it is multiple through protrusion（14）Aperture（19）.
- 2. a kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape according to claim 1 is used Fixture, it is characterised in that：Two installing plates in the aerofoil profile module（16）Structure is identical.
- 3. a kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape according to claim 1 is used Fixture, it is characterised in that：The locking short screw（17）With locking long spiro nail（18）On be threaded with locking nut （20）.
- 4. a kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape according to claim 1 is used Fixture, it is characterised in that：Laterally adjacent two apertures（19）Between spacing, longitudinally adjacent two apertures（19）Between Spacing be 7 ~ 8mm.
- 5. a kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape according to claim 4 is used Fixture, it is characterised in that：The aperture（19）A diameter of 2~3mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720703821.0U CN207227293U (en) | 2017-06-16 | 2017-06-16 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720703821.0U CN207227293U (en) | 2017-06-16 | 2017-06-16 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207227293U true CN207227293U (en) | 2018-04-13 |
Family
ID=61852964
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720703821.0U Active CN207227293U (en) | 2017-06-16 | 2017-06-16 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207227293U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107266099A (en) * | 2017-06-16 | 2017-10-20 | 中国人民解放军第五七九工厂 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
| CN112571217A (en) * | 2020-12-04 | 2021-03-30 | 江苏源清动力技术有限公司 | Turbine blade grinding clamping frock |
-
2017
- 2017-06-16 CN CN201720703821.0U patent/CN207227293U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107266099A (en) * | 2017-06-16 | 2017-10-20 | 中国人民解放军第五七九工厂 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
| CN112571217A (en) * | 2020-12-04 | 2021-03-30 | 江苏源清动力技术有限公司 | Turbine blade grinding clamping frock |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107266099A (en) | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture | |
| US7223465B2 (en) | SiC/SiC composites incorporating uncoated fibers to improve interlaminar strength | |
| EP2540975B1 (en) | Method of forming a hybrid part made from monolithic ceramic skin and CMC core | |
| CA2747364C (en) | Ceramic matrix composite blade having integral platform structures and methods of fabrication | |
| CN106977217B (en) | A kind of preparation method of high-strength and high-ductility silicon carbide fiber reinforced silicon carbide ceramic matric composite | |
| CN106957180B (en) | Cf/C-SiC composite material and preparation method and application thereof | |
| CN106565261B (en) | A kind of method that precursor infiltration and pyrolysis method prepares SiC/SiC composite material pin | |
| US6280550B1 (en) | Fabrication of composite articles having an infiltrated matrix | |
| US8980435B2 (en) | CMC component, power generation system and method of forming a CMC component | |
| CN105367105B (en) | The method that machining auxiliary CVI prepares thicker-walled ceramic based composites | |
| EP3689840B1 (en) | A method for forming a ceramic matrix composite | |
| CN102180695B (en) | Wave-absorbing ceramic made of silicon carbide composite material and preparation method thereof | |
| CN108191432B (en) | Connection method of SiC/SiC composite material | |
| CN207227293U (en) | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture | |
| CN109688643B (en) | Manufacturing method of carbon-carbon heater | |
| JP6887454B2 (en) | Composite components with T or L-shaped joints and methods for forming them | |
| CN110078516A (en) | The quasi-isotropic SiC of high-volume fractional short fiber reinforcedfThe preparation method of/SiC ceramic matrix composite material | |
| CN111018534A (en) | Preparation method of ceramic matrix composite material component with abradable coating and component | |
| CN110981520A (en) | Preparation method of ceramic matrix composite material component with abradable coating and component | |
| CN105622125B (en) | The preparation process of carbon fiber reinforced carbon matrix-Connecting Part of Ceramic-Based Compound Material | |
| CN103274714B (en) | Improved Z-pin method for two-dimensional ceramic matrix composite | |
| CN112125673B (en) | Method for preparing right-angle stringer based on precursor impregnation cracking process | |
| CN114427481A (en) | Ceramic matrix composite turbine rotor blade with internal cooling channels, mold and preparation method | |
| US20040115348A1 (en) | Method for processing silicon-carbide preforms having a high temperature boron nitride coating | |
| CN111892405A (en) | Preparation method for preparing ceramic matrix composite material by interface-layer-free process |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: No. 10 high tech Zone Gaopeng road in Chengdu city of Sichuan Province in 610041 Patentee after: State-run West Sichuan machine factory Address before: No.10 Gaopeng Avenue, high tech Zone, Chengdu, Sichuan 610000 Patentee before: PLA NO.5719 FACTORY |
|
| CP03 | Change of name, title or address |