CN107266099A - 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
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- CN107266099A CN107266099A CN201710457867.3A CN201710457867A CN107266099A CN 107266099 A CN107266099 A CN 107266099A CN 201710457867 A CN201710457867 A CN 201710457867A CN 107266099 A CN107266099 A CN 107266099A
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- Prior art keywords
- module
- aerofoil profile
- listrium
- blade
- leaf basin
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Classifications
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
Abstract
The invention 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）The cavity A being engaged（8）, small listrium module（5）Bottom be provided with and small listrium（2）The cavity B being engaged（11）, blade back aerofoil profile module（6）Rear side be provided with and blade back aerofoil profile（21）The curved surface being engaged（12）, leaf basin aerofoil profile module（7）Front side be provided with and leaf basin aerofoil profile（22）The projection being engaged（14）.The beneficial effects of the invention are as follows：Ensure finished product front side of vane without or the processing of few surplus, fast assembling-disassembling and assembling, effectively realize that the near-net-shape of ceramic matrix composite turbine stator blade, manufacturing cost are low.
Description
Technical field
The present invention relates to technical field of aircraft engine part manufacture is belonged to, particularly a kind of aero-engine ceramic base
Composite turbine stator blade near-net-shape fixture.
Background technology
Ceramic matrix composite turbine stator blade is as one of part of aero-engine most critical, because 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 most possibly replaces nickel-base high-temperature because of the premium properties 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 is used at a higher temperature is ceramic matric composite.Ceramic matric composite one
As refer to carbon fiber reinforced carbon matrix（C/C）Composite, carbon fibre reinforced silicon carbide ceramic base（C/SiC）Composite, carborundum
Silicon carbide fiber reinforced ceramic base（SiC/SiC）Composite, is a kind of superhigh temperature composite, and operating temperature is up to 1650
℃。
At present, ceramic matrix composite turbine stator blade is typically prepared process for blade precast body braiding → chemistry gas
Mutually ooze product（Chemical vapor infiltration, CVI）Boundary layer → matrix densification（Using CVI and PIP technologies）→
Machining → 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 use 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 requires near-net-shape（I.e. preparation process Leaf does not allow or allows machinery on a small quantity
Processing）.But it is relatively soft by the blade precast body of fibrage, and can not possibly reach three-dimensional aerofoil profile of blade 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 ensure card, it may appear that warpage, distortion, projection 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）.
The content of the invention
It is an object of the invention to overcome the shortcoming of prior art there is provided one kind ensure finished product front side of vane without or it is few remaining
Amount processing, fast assembling-disassembling and assembling, near-net-shape, the manufacturing cost for effectively realizing ceramic matrix composite turbine stator blade
Low aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture.
The purpose of the present invention is achieved through the following technical solutions：A kind of aero-engine ceramic matrix composite turbine is led
To device blade near-net-shape fixture, it includes big listrium module, small listrium module, blade back aerofoil profile module and leaf basin aerofoil profile mould
It is provided with the top of block, described big listrium module in the cavity A being engaged with the big listrium of blade precast body, big listrium module also
The blade back locating piece and leaf basin locating piece for being located at cavity A left and right sides respectively are provided with, blade back locating piece is located at leaf basin locating piece
Front side, the bottom of described small listrium module is provided with the cavity B being engaged with small listrium；After described blade back aerofoil profile module
Side is provided with the curved surface being engaged with blade back aerofoil profile, and the bottom of blade back aerofoil profile module offers the first positioning hole, blade back aerofoil profile mould
Block is positioned in big listrium module and the first positioning hole is engaged with blade back locating piece；Set on front side of described leaf basin aerofoil profile module
The projection being engaged with leaf basin aerofoil profile is equipped with, the bottom of leaf basin aerofoil profile module offers the second positioning hole, and leaf basin aerofoil profile module is put
It is placed in big listrium module and the second positioning hole is engaged with leaf basin locating piece；Described leaf basin aerofoil profile module and blade back aerofoil profile mould
The left and right sides of block 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 edge
Between plate module, locking short screw, leaf are 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 mould are provided between basin aerofoil profile module, big listrium module and small listrium module
Locking long spiro nail is provided between block and small listrium module；Described big listrium module is distributed with multiple connection chambers in appearance
Multiple connection cavity B aperture, the front of blade back aerofoil profile module are distributed with body A aperture, the outer surface of small listrium module
It is distributed with and multiple apertures through projection is provided with behind multiple apertures through curved surface, leaf basin aerofoil profile module.
Two mounting plates structures in described aerofoil profile module are identical.
Locking nut is threaded with described locking short screw and locking long spiro nail.
The spacing between spacing, longitudinally adjacent two apertures between described laterally adjacent two apertures is 7 ~ 8mm.
A diameter of 2~3mm of described aperture.
The present invention has advantages below：（1）The four big moulds that the present invention is designed by using high-temperature alloy or graphite material
Block, then coordinated using the screw tightened with nut and exert a force, it is fixed and compress, be compacted blade precast body, be blade near net-shape into
Type provides advantage.（2）This fixture ensure that front side of vane without or the processing of few surplus, it is to avoid the three-dimensional of destruction blade
Fiber weave structure and reduction Blade Properties index is avoided, improve blade and prepare quality and production efficiency.
Brief description of the drawings
Fig. 1 is the structural representation of blade precast body；
Fig. 2 is Fig. 1 right view；
Fig. 3 is structural representation of the invention；
Fig. 4 removes the structural representation after blade back aerofoil profile module, leaf basin aerofoil profile module for the present invention；
Fig. 5 removes the structural representation after big listrium module, small listrium module for the present invention；
Fig. 6 is the structural representation of big listrium module；
Fig. 7 is the structural representation of small listrium module；
Fig. 8 is the structural representation of blade back aerofoil profile module；
Fig. 9 is Fig. 8 upward view；
Figure 10 is the structural representation of leaf basin aerofoil profile module；
Figure 11 Figure 10 upward view；
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 modules, 7-
Leaf basin aerofoil profile module, 8- cavitys A, 9- blade back locating piece, 10- leaf basin locating pieces, 11- cavitys B, 12- curved surface, 13- first is positioned
Hole, 14- is raised, the positioning holes of 15- second, 16- installing plates, 17- locking short screws, 18- locking long spiro nails, 19- apertures, 20- locks
Tight nut, 21- blade back aerofoil profiles, 22- leaf basin aerofoil profiles.
Embodiment
The present invention will be further described below in conjunction with the accompanying drawings, and protection scope of the present invention is not limited to as described below：
As shown in Fig. 3 ~ 11, a kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture, it
Including big listrium module 4, small listrium module 5, blade back aerofoil profile module 6 and leaf basin aerofoil profile module 7, described big listrium module 4
Top is provided with the cavity A8 being engaged with the big listrium of blade precast body 3, big listrium module 4 to be additionally provided with is located at cavity respectively
The blade back locating piece 9 and leaf basin locating piece 10 of A8 left and right sides, blade back locating piece 9 are located at the front side of leaf basin locating piece 10, described
The bottom of small listrium module 5 is provided with the cavity B11 being engaged with small listrium 2；The rear side of described blade back aerofoil profile module 6 is set
There is the curved surface 12 being engaged with blade back aerofoil profile 21, the bottom of blade back aerofoil profile module 6 offers the first positioning hole 13, blade back aerofoil profile mould
Block 6 is positioned in big listrium module 4 and the first positioning hole 13 is engaged with blade back locating piece 9；Described leaf basin aerofoil profile module 7
Front side is provided with the projection 14 being engaged with leaf basin aerofoil profile 22, and 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 positioning hole 15 is engaged with leaf basin locating piece 10；The described leaf basin wing
Pattern block 7 and the left and right sides of blade back aerofoil profile module 6 are fixedly provided with installing plate 16, leaf basin aerofoil profile module 7 and blade back aerofoil profile module 6
It may be contained between big listrium module 4 and small listrium module 5, installing plate 16 and the blade back aerofoil profile module 6 of leaf basin aerofoil profile module 7
Locking short screw 17 is provided between installing plate 16, is set between leaf basin aerofoil profile module 7, big listrium module 4 and small listrium module 5
Have and be threaded with locking nut 20, and blade back aerofoil profile on locking long spiro nail 18, locking short screw 17 and locking long spiro nail 18
Locking long spiro nail 18 is provided between module 6, big listrium module 4 and small listrium module 5；The appearance of described big listrium module 4
On be distributed with multiple connection cavity A8 apertures 19, the outer surface of small listrium module 5 and be distributed with multiple connection cavity B11
Aperture 19, the front of blade back aerofoil profile module 6 is distributed with behind multiple apertures 19 through curved surface 12, leaf basin aerofoil profile module 7
It is provided with multiple apertures 19 through projection 14.The main function of aperture：1st, CVI prepares boundary layer or matrix densification process
In there is provided passage make reacting gas enter blade precast body on reactive deposition ceramic matrix；2nd, there is provided passage in PIP densifications
Enter reaction solution to be impregnated on blade precast body, then make reacted useless gas there is provided passage in Pintsch process
Precursor reactant thing is discharged from blade precast body.
Two structures of installing plate 16 in described aerofoil profile module are identical.Between described laterally adjacent two apertures 19
Spacing between spacing, longitudinally adjacent two apertures 19 is 7 ~ 8mm；A diameter of 2~3mm of described 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, structure such as Fig. 1 of blade precast body with
Shown in 2.
S2, turbine nozzle vane precast body is placed in vacuum high-temperature heat-treatment furnace to progress high temperature pretreatment, pre- place
700 DEG C~2400 DEG C of the temperature of reason, time are 1h~3h, protected using vacuum or inert gas that 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 the cavity of small listrium module 5
B11 is engaged with the small listrium 2 of blade precast body, it is ensured that blade precast body placing direction and both be smooth connection, it is impossible to go out
Now be uneven problem；The cavity A8 of big listrium module 4 is engaged with the big listrium 3 of blade precast body, it is ensured that blade is prefabricated
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 module
On 4, blade back locating piece 9 is assembled in the first positioning hole 13 of blade back aerofoil profile module 6, to determine big listrium module 4, blade back aerofoil profile
Relative position between module 6 and blade precast body；Blade back aerofoil profile module 6, small listrium module 5, big listrium module 4 are passed through into lock
Tight long spiro nail 18 is connected；Leaf basin locating piece 10 is assembled in big listrium module 4, leaf basin locating piece 10 is assembled to leaf basin aerofoil profile mould
In second positioning hole 15 of block 7, with determine small listrium module 5, big listrium module 4, leaf basin aerofoil profile module 7 and blade precast body it
Between relative position；Leaf basin aerofoil profile module 7, small listrium module 5, big listrium module 4 are connected by locking long spiro nail 18；Using
Locking short screw 17 is connected to fix blade back aerofoil profile module 6, leaf basin aerofoil profile module 7 with locking nut 20；Tighten locking long spiro nail
Locking nut 20 on 18, to be compacted, compress blade precast body, realizes the Rapid tooling of blade precast body, so as to ensure that
The compact dimensions of 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 interfaces
Prepared by layer, boundary layer includes pyrolysis carbon boundary layer and BN boundary layers.CVI prepares pyrolysis carbon boundary layer and uses methane or propane and day
Right gas prepares BN boundary layers and uses NH as reacting gas, CVI3Gas and BCl3Gas is as reacting gas, and reacting gas is through folder
Aperture 19 on tool is passed through in fixture, and CVI preparation temperatures are 700 DEG C~1100 DEG C, the time is 0.5h~4h.
S4, due to being prepared after boundary layer using CVI, 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）Blade precast body through processing in step S3 is taken out and loaded in another fixture, frock mode and S3（I）Phase
Together；
S4（II）The fixture combination body that will be equipped with blade precast body is fitted into CVI stoves or PIP stoves, is carried out using technology of preparing parameter
Prepared by ceramic matrix densification, ceramic matrix includes C and SiC.CVI prepares C matrix and uses methane or propane and natural gas conduct
Reacting gas, CVI prepares SiC matrix and uses trichloromethyl silane（CH3SiCl3）、H2Gas and BCl3Gas is used as reaction gas
Body, 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 carry out in vacuum high-temperature treatment furnace Pintsch process（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, blade is checked after taking-up
Whether 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 shaping
Repeat step S4（II）；
S5, turbine nozzle vane precast body final matrix densification, are to reach the prefabricated volume density of turbine nozzle vane
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 is prefabricated
The final ceramic matrix densification of body should be the supplement process of its initial stage matrix densification preparation, both reacting gas, system
The preparation conditions such as standby parameter, preparation process are identical, and simply the former preparation time is longer, such as using CVI prepare C matrix or
SiC matrix, its preparation time should be 200h~600h；Or as using PIP prepare SiC matrix, iterative cycles number of times should be 9 times~
13 times.
S5（II）Blade precast body is taken out from CVI stoves or PIP stoves, now the prefabricated volume density of turbine nozzle vane has been
Up to finally density is required, complete matrix densification, is hardened and shapes completely, it has also become ceramic matrix composite vane hair
Base；
S6, ceramic matrix composite vane blank machining.Due to step S5（II）Middle ceramic matrix composite vane hair
The working face size of base 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 must such as 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；
S8, ceramic matrix composite turbine stator blade inspection and examination.After process made above, ceramic base is combined
Material turbine nozzle vane has completed all preparation process, must be checked and be checked and accepted by blade design drawing requirement, passed through
It is qualified ceramic matrix composite turbine stator blade finished parts afterwards.
Because the top of big listrium module 4 is provided with the cavity A8 being engaged with the big listrium of blade precast body 3, small listrium mould
The bottom of block 5 is provided with the cavity B11 being engaged with small listrium 2, and the rear side of blade back aerofoil profile module 6 is provided with and blade back aerofoil profile 21
The curved surface 12 being engaged, the front side of leaf basin aerofoil profile module 7 is provided with the projection 14 being engaged with leaf basin aerofoil profile 22, carry out near net into
During type, it is ensured that front side of vane without or the processing of few surplus, it is to avoid the three-dimensional fiber braiding structure of destruction 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)
1. a kind of 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）, described big listrium
Module（4）Top be provided with and the big listrium of blade precast body（3）The cavity A being engaged（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, described small listrium module（5）Bottom be provided with and small listrium（2）The cavity B being engaged
（11）；Described blade back aerofoil profile module（6）Rear side be provided with and blade back aerofoil profile（21）The curved surface being engaged（12）, blade back aerofoil profile
Module（6）Bottom offer the first positioning hole（13）, blade back aerofoil profile module（6）It is positioned over big listrium module（4）It is upper and first
Positioning hole（13）With blade back locating piece（9）It is engaged；Described leaf basin aerofoil profile module（7）Front side be provided with and leaf basin aerofoil profile
（22）The projection being engaged（14）, leaf basin aerofoil profile module（7）Bottom offer the second positioning hole（15）, leaf basin aerofoil profile module
（7）It is positioned over big listrium module（4）Upper and the second positioning hole（15）With leaf basin locating piece（10）It is engaged；Described 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）；Described 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 it is multiple run through curved surface（12）Aperture（19）, leaf basin aerofoil profile module
（7）Behind be provided with it is multiple through projection（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 described 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：Described 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：Described 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：Described aperture（19）A diameter of 2~3mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710457867.3A CN107266099B (en) | 2017-06-16 | 2017-06-16 | Clamp for near-net forming of ceramic matrix composite turbine guide vane of aero-engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710457867.3A CN107266099B (en) | 2017-06-16 | 2017-06-16 | Clamp for near-net forming of ceramic matrix composite turbine guide vane of aero-engine |
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| CN107266099A true CN107266099A (en) | 2017-10-20 |
| CN107266099B CN107266099B (en) | 2023-07-18 |
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| CN109650924A (en) * | 2019-02-26 | 2019-04-19 | 西北工业大学 | Based on SiC fiber ceramics based composites turbine blisks preparation method |
| CN111102017A (en) * | 2019-12-13 | 2020-05-05 | 西安鑫垚陶瓷复合材料有限公司 | Aeroengine ceramic matrix composite fixed guider blade structure and forming method thereof |
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| CN115093231A (en) * | 2022-06-23 | 2022-09-23 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with tail edge cleft and preparation method thereof |
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Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0375588A1 (en) * | 1988-11-10 | 1990-06-27 | Lanxide Technology Company, Lp. | Methods of forming metal matrix composite bodies by a spontaneous infiltration process |
| JP2002036102A (en) * | 2000-07-28 | 2002-02-05 | Ibiden Co Ltd | Wafer holding jig |
| JP2003261381A (en) * | 2002-03-06 | 2003-09-16 | Ishikawajima Harima Heavy Ind Co Ltd | Ceramic-base composite member and method for producing the same |
| US6648597B1 (en) * | 2002-05-31 | 2003-11-18 | Siemens Westinghouse Power Corporation | Ceramic matrix composite turbine vane |
| US20040171330A1 (en) * | 2003-02-28 | 2004-09-02 | Whitmarsh Robert Duane | Apparatus and method for consistently retaining a gas turbine engine blade in a predetermined position and orientation |
| JP2005183127A (en) * | 2003-12-18 | 2005-07-07 | Tdk Corp | Processing method for ceramic plate, fixture for fixing ceramic plate and manufacturing method for spacer for flat panel display |
| CN101042055A (en) * | 2005-12-22 | 2007-09-26 | 通用电气公司 | Composite blading member and method for making |
| EP2181974A1 (en) * | 2008-10-31 | 2010-05-05 | AVIO S.p.A. | Method for the production of components made of ceramic-matrix composite material |
| WO2010110325A1 (en) * | 2009-03-26 | 2010-09-30 | 株式会社Ihi | Cmc turbine stator vane |
| JP2010215459A (en) * | 2009-03-17 | 2010-09-30 | Ihi Corp | Method for manufacturing structure, and the structure |
| US20110259506A1 (en) * | 2010-04-21 | 2011-10-27 | Rolls-Royce Plc | Method of manufacturing a ceramic matrix composite article |
| US20120279631A1 (en) * | 2009-11-13 | 2012-11-08 | Ihi Corporation | Method for manufacturing vane |
| CN102773733A (en) * | 2012-07-18 | 2012-11-14 | 西安航空动力股份有限公司 | Method and clamp for moulding surface positioning clamping of finish forge blade |
| US20130323073A1 (en) * | 2012-06-05 | 2013-12-05 | Michael G. McCaffrey | Assembled blade platform |
| CN204622394U (en) * | 2015-03-16 | 2015-09-09 | 天津工业大学 | A kind of carbon fiber cell type prefabricated component is made and is used shaper |
| US20160167269A1 (en) * | 2013-07-29 | 2016-06-16 | Safran | Method of fabricating a composite material blade having an integrated metal leading edge for a gas turbine aeroengine |
| WO2017060601A1 (en) * | 2015-10-05 | 2017-04-13 | Safran Aircraft Engines | Process for manufacturing a ceramic composite material part by pressurized injection of a loaded slurry into a porous mould |
| CN106747534A (en) * | 2016-11-16 | 2017-05-31 | 中国人民解放军第五七九工厂 | A kind of aero-engine ceramic base diaphragm seal and preparation method thereof |
| CN106747531A (en) * | 2016-05-30 | 2017-05-31 | 北京航空航天大学 | A kind of polynary carbon and ceramic base thermostructural composite and its turbo blade without surplus preparation method |
| CN207227293U (en) * | 2017-06-16 | 2018-04-13 | 中国人民解放军第五七一九工厂 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
-
2017
- 2017-06-16 CN CN201710457867.3A patent/CN107266099B/en active Active
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0375588A1 (en) * | 1988-11-10 | 1990-06-27 | Lanxide Technology Company, Lp. | Methods of forming metal matrix composite bodies by a spontaneous infiltration process |
| JP2002036102A (en) * | 2000-07-28 | 2002-02-05 | Ibiden Co Ltd | Wafer holding jig |
| JP2003261381A (en) * | 2002-03-06 | 2003-09-16 | Ishikawajima Harima Heavy Ind Co Ltd | Ceramic-base composite member and method for producing the same |
| US6648597B1 (en) * | 2002-05-31 | 2003-11-18 | Siemens Westinghouse Power Corporation | Ceramic matrix composite turbine vane |
| US20040171330A1 (en) * | 2003-02-28 | 2004-09-02 | Whitmarsh Robert Duane | Apparatus and method for consistently retaining a gas turbine engine blade in a predetermined position and orientation |
| JP2005183127A (en) * | 2003-12-18 | 2005-07-07 | Tdk Corp | Processing method for ceramic plate, fixture for fixing ceramic plate and manufacturing method for spacer for flat panel display |
| CN101042055A (en) * | 2005-12-22 | 2007-09-26 | 通用电气公司 | Composite blading member and method for making |
| EP2181974A1 (en) * | 2008-10-31 | 2010-05-05 | AVIO S.p.A. | Method for the production of components made of ceramic-matrix composite material |
| JP2010215459A (en) * | 2009-03-17 | 2010-09-30 | Ihi Corp | Method for manufacturing structure, and the structure |
| WO2010110325A1 (en) * | 2009-03-26 | 2010-09-30 | 株式会社Ihi | Cmc turbine stator vane |
| US20120279631A1 (en) * | 2009-11-13 | 2012-11-08 | Ihi Corporation | Method for manufacturing vane |
| US20110259506A1 (en) * | 2010-04-21 | 2011-10-27 | Rolls-Royce Plc | Method of manufacturing a ceramic matrix composite article |
| US20130323073A1 (en) * | 2012-06-05 | 2013-12-05 | Michael G. McCaffrey | Assembled blade platform |
| CN102773733A (en) * | 2012-07-18 | 2012-11-14 | 西安航空动力股份有限公司 | Method and clamp for moulding surface positioning clamping of finish forge blade |
| US20160167269A1 (en) * | 2013-07-29 | 2016-06-16 | Safran | Method of fabricating a composite material blade having an integrated metal leading edge for a gas turbine aeroengine |
| CN204622394U (en) * | 2015-03-16 | 2015-09-09 | 天津工业大学 | A kind of carbon fiber cell type prefabricated component is made and is used shaper |
| WO2017060601A1 (en) * | 2015-10-05 | 2017-04-13 | Safran Aircraft Engines | Process for manufacturing a ceramic composite material part by pressurized injection of a loaded slurry into a porous mould |
| CN106747531A (en) * | 2016-05-30 | 2017-05-31 | 北京航空航天大学 | A kind of polynary carbon and ceramic base thermostructural composite and its turbo blade without surplus preparation method |
| CN106747534A (en) * | 2016-11-16 | 2017-05-31 | 中国人民解放军第五七九工厂 | A kind of aero-engine ceramic base diaphragm seal and preparation method thereof |
| CN207227293U (en) * | 2017-06-16 | 2018-04-13 | 中国人民解放军第五七一九工厂 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
Non-Patent Citations (1)
| Title |
|---|
| 李志永: "发动机叶片电解加工夹具结构设计与密封性能分析", 《润滑与密封》, no. 01, pages 139 - 142 * |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109650924A (en) * | 2019-02-26 | 2019-04-19 | 西北工业大学 | Based on SiC fiber ceramics based composites turbine blisks preparation method |
| CN111102017A (en) * | 2019-12-13 | 2020-05-05 | 西安鑫垚陶瓷复合材料有限公司 | Aeroengine ceramic matrix composite fixed guider blade structure and forming method thereof |
| CN111102017B (en) * | 2019-12-13 | 2022-07-12 | 西安鑫垚陶瓷复合材料有限公司 | Aeroengine ceramic matrix composite fixed guider blade structure and forming method thereof |
| CN112552068A (en) * | 2020-11-26 | 2021-03-26 | 西安鑫垚陶瓷复合材料有限公司 | Protection tool and method for rivet welding of C/SiC-ZrC and C/SiC ceramic matrix composite |
| CN112552068B (en) * | 2020-11-26 | 2022-12-20 | 西安鑫垚陶瓷复合材料有限公司 | Protection tool and method for rivet welding of C/SiC-ZrC and C/SiC ceramic matrix composite |
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| CN115093231A (en) * | 2022-06-23 | 2022-09-23 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with tail edge cleft and preparation method thereof |
| CN115093231B (en) * | 2022-06-23 | 2023-09-01 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with trailing edge split joint and preparation method thereof |
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