CN103936450A - Preparation method for sharp leading edge - Google Patents
Preparation method for sharp leading edge Download PDFInfo
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- CN103936450A CN103936450A CN201410116151.3A CN201410116151A CN103936450A CN 103936450 A CN103936450 A CN 103936450A CN 201410116151 A CN201410116151 A CN 201410116151A CN 103936450 A CN103936450 A CN 103936450A
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Abstract
The invention relates to a preparation method for a sharp leading edge possessing a fiber prefabricated body inner core surface coated with a two-dimension laminated carbon-fiber protection layer. The two-dimension laminated carbon-fiber protection layer is used to coat the prefabricated body inner core, so that local hot-fluid concentration of the prefabricated body inner core caused by fiber cracking and needle dropping because of mechanic processing is eliminated, and the erosion-corrosion resistant performance of the prepared composite material sharp leading edge is improved. Because the fiber prefabricated body inner core surface is coated with the two-dimension laminated carbon-fiber protection layer, the protection layer is tightly attached to the processed prefabricated body inner core, the protection layer does not need mechanical processing, the surface is complete and has no tiny projections and depressions, and by taking the protection layer surface as the radial surface of the sharp leading edge, the influence on aerodynamic heating caused by needle dropping and fiber cracking of the prefabricated body inner core is eliminated, and the prepared composite material sharp leading edge has good erosion-corrosion resistant performance.
Description
Technical field
The present invention relates to the sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of a kind of fiber preform core surface, improve the antiscour that the sharp-pointed leading edge of prepared matrix material is on active service under hot environment and degrade performance.
Background technology
Continuous fibre toughened silicon carbide composite material (C/SiC) is a kind of desirable high-temperature structural material, has the series of advantages such as high temperature resistant, low density, high strength, anti-thermal shock, has wide practical use in Aeronautics and Astronautics field.By matrix modification, introduce different high-temperature-phases, can improve greatly the high temperature Burning corrosion resistance energy of C/SiC, improve its service life and quality under harsh Aerodynamic Heating environment.
The precast body of preparation C/SiC matrix material has multiple, as 2D cloth lamination, 2.5D and 3D braiding structure and multidirectional braiding structure etc.Common Single Fiber braiding structure can not finely meet the preparation requirement of sharp-pointed leading edge precast body, especially to small curvature radius leading edge (<3mm), is difficult to the radius curved surface of the sharp-pointed leading edge precast body of perfect braiding; If obtain radius curved surface through suitable mechanical workout, cutting or polishing, can cause leading-edge radius position occur fibre breakage and fall pin situation, form small projection and pit in leading edge surface.The heat flow density that Aerodynamic Heating produces and 0.5 power of stationary point radius are inversely proportional to, and stationary point radius is less, and heat flow density is larger; The projection of leading edge surface and pit are equivalent to small stationary point radius, cause larger hot-fluid in Aerodynamic Heating, cause the serious ablation at this position.
In the time that sharp-pointed leading edge is prepared protective layer; if adopt common braiding structure to be difficult to the sharp-pointed leading edge of braiding, leading edge surface there will be fibre breakage and falls pin situation in the time of machine-shaping, forms small projection and pit in leading edge surface; in Aerodynamic Heating, cause that huge hot-fluid is concentrated, cause serious ablation.
Summary of the invention
The technical problem solving
For fear of the deficiencies in the prior art part; the present invention proposes the sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of a kind of fiber preform core surface; with the coated precast body inner core of two-dimension laminate carbon fiber protective layer; eliminate the fibre breakage that precast body inner core causes due to mechanical workout and fall the local heat flux that pin causes and concentrate, the antiscour that improves the sharp-pointed leading edge of matrix material of preparation degrades performance.
Technical scheme
A sharp-pointed leading edge preparation method for the coated two-dimension laminate carbon fiber protective layer of fiber preform core surface, is characterized in that step is as follows:
Step 1, making mould: the design paper according to sharp-pointed leading edge member is made formpiston and former, between formpiston and former, leaves space; Described former internal surface radius curved surface coincide with the leading-edge radius curved surface of sharp-pointed leading edge member;
Step 2, prepare two-dimension laminate carbon fiber protective layer: lamination carbon cloth is laid in to male mold surfaces, adopts fiber that carbon cloth is firmly sewed up fixing by position, hole reserved on mould; Adopt CVI process deposits RESEARCH OF PYROCARBON and SiC, fix protective layer shape, after the demoulding, obtain the housing of two-dimension laminate carbon fiber protective layer;
The thickness of described lamination carbon cloth is die clearance thickness;
Step 3, prepare fiber preform inner core:
Adopt CVI densifying method to prepare carbon-fiber reinforced carbon C/C or carbon fibre reinforced silicon carbide C/SiC precast body, its density is controlled at 1.2g/cm
3-1.8g/cm
3scope, carries out mechanical workout by the inner core size of sharp-pointed leading edge member to precast body, obtains sharp-pointed leading edge fiber preform inner core;
Step 4, group two-dimension laminate carbon fiber protective layer and fiber preform inner core close: in housing and the punching of inner core corresponding position, adopt C/SiC pin by housing and inner core combination, obtain sharp-pointed leading edge precast body;
Step 5, prepare sharp-pointed leading edge: adopt CVI technique to the further densification of sharp-pointed leading edge precast body, obtain the sharp-pointed leading edge of final matrix material.
With the preparation of CVI carbon-fiber reinforced carbon C/C or the carbon fibre reinforced silicon carbide C/SiC precast body of PIP densifying method step of replacing 3.
With the further densification process of the sharp-pointed leading edge precast body of CVI of PIP or RMI technique step of replacing 5.
Space between described formpiston and former is 1～2mm.
Described moulding stock is graphite material.
Described former thickness is 5～10mm; Described formpiston size is identical with precast body inner core.
Beneficial effect
The sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of a kind of fiber preform core surface that the present invention proposes; with the coated precast body inner core of two-dimension laminate carbon fiber protective layer; eliminate the fibre breakage that precast body inner core causes due to mechanical workout and fall the local heat flux that pin causes and concentrate, the antiscour that improves the sharp-pointed leading edge of matrix material of preparation degrades performance.Owing to being coated two-dimension laminate carbon fiber protective layer in fiber preform core surface; make protective layer fit tightly the precast body inner core through processing; protective layer is without carrying out mechanical workout; surface is complete; without small projection and pit; radius surface using it as sharp-pointed leading edge, that can eliminate precast body inner core falls pin and the impact of fibre breakage on Aerodynamic Heating, makes the sharp-pointed leading edge of matrix material of preparation have good antiscour to degrade performance.
Brief description of the drawings
Fig. 1 graphite jig photo.
Fig. 2 protective layer photo.
The sharp-pointed leading edge precast body full face that Fig. 3 is prepared.
The sharp-pointed leading edge precast body side photo that Fig. 4 is prepared.
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
Embodiment 1:
Leading-edge radius is 1.5mm, and inner core material is the sharp-pointed C/SiC-ZrC leading edge of three-dimensional acupuncture C/SiC, and preparation process is as follows:
Mould preparation: adopt graphite material, according to leading edge design paper processing mold, formpiston leading-edge radius is R0.5mm, and former internal surface radius is R1.5mm, and formpiston former correspondence position leaves circular hole, and diameter is 5mm, apart from being uniformly distributed under the 15mm of leading-edge radius top.
Two-dimension laminate protective layer preparation: by the male mold surfaces that is laid on smooth 5 layers of carbon cloth, by Kong Weiyong fiber reserved on mould, carbon cloth is firmly sewed up fixing.Adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is written into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, the protective layer housing of acquisition moulding.Stitching, with cutting into the demoulding of wide 25mm block after carbon fiber polishing, is obtained to 2D-C/SiC protective layer housing.
Fiber preform inner core preparation: be 1.7g/cm by density
3three-dimensional acupuncture C/SiC sheet material be dimensioned to the block of wide 25mm according to inner core, leading-edge radius is R0.5mm.
Two-dimension laminate carbon fiber protective layer combines with fiber preform inner core: beat at housing and the corresponding position of inner core the hole that diameter is 3.5mm, adopt C/SiC pin by housing and inner core combination, obtain leading edge precast body.
Sharp-pointed leading edge preparation: adopt VPI in conjunction with RMI method, vacuum pressure infiltration resol slurry in precast body, vacuum tightness is-0.08MPa that pressure is 0.8MPa, 150 DEG C solidify after at 900 DEG C cracking resin finally at 1700 DEG C, infiltrate silicon-zirconium, obtain C/SiC-ZrC sharp-pointed leading edge.
Embodiment 2:
Leading-edge radius is 2mm, and inner core material is the C/SiC leading edge of 3 dimension acupuncture C/SiC, and preparation process is as follows:
Mould preparation: adopt graphite material, according to leading edge design paper processing mold, formpiston leading-edge radius is R1mm, and former internal surface radius is R2mm, and formpiston former correspondence position leaves circular hole, and diameter is 5mm, apart from being uniformly distributed under the 15mm of leading-edge radius top.
Two-dimension laminate protective layer preparation: by the male mold surfaces that is laid on smooth 5 layers of carbon cloth, by Kong Weiyong fiber reserved on mould, carbon cloth is firmly sewed up fixing.Adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is written into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, the protective layer housing of acquisition moulding.Stitching, with cutting into the demoulding after wide 25mm piece after carbon fiber polishing, is obtained to 2D-C/SiC protective layer housing.
Fiber preform inner core preparation: be 1.7g/cm by density
3three-dimensional acupuncture C/SiC sheet material be processed into the block of wide 25mm according to cavity dimension, leading-edge radius is R1mm.
Two-dimension laminate carbon fiber protective layer combines with fiber preform inner core: beat at housing and the corresponding position of inner core the hole that diameter is 3.5mm, adopt C/SiC pin by housing and inner core combination, obtain leading edge precast body.
Sharp-pointed leading edge preparation: adopt CVI method, utilize hydrogen that MTS is written into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, depositing silicon carbide matrix in leading edge precast body, obtains the sharp-pointed leading edge of C/SiC.
Embodiment 3:
Leading-edge radius is 1.5mm, and inner core material is the sharp-pointed leading edge of C/SiC of 3 dimension puncture C/SiC, and preparation process is as follows:
Mould preparation: adopt graphite material, according to leading edge design paper processing mold, formpiston leading-edge radius is R0.5mm, and former internal surface radius is R1.5mm, and formpiston former correspondence position leaves circular hole, and diameter is 5mm, apart from being uniformly distributed under the 15mm of leading-edge radius top.
Two-dimension laminate protective layer preparation: by the male mold surfaces that is laid on smooth 5 layers of carbon cloth, by Kong Weiyong fiber reserved on mould, carbon cloth is firmly sewed up fixing.Adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is written into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, the protective layer housing of acquisition moulding.Stitching, with cutting into the demoulding after wide 25mm piece after carbon fiber polishing, is obtained to 2D-C/SiC protective layer housing.
Fiber preform inner core preparation: be 1.7g/cm by density
3three-dimensional acupuncture C/SiC sheet material be processed into the block of wide 25mm according to cavity dimension, leading-edge radius is R0.5mm.
Two-dimension laminate carbon fiber protective layer combines with fiber preform inner core: beat at housing and the corresponding position of inner core the hole that diameter is 3.5mm, adopt C/SiC pin by housing and inner core combination, obtain leading edge precast body.
Sharp-pointed leading edge preparation: adopt PIP in conjunction with RMI method, vacuum pressure infiltration furane resin slurry in precast body, vacuum tightness is-0.08MPa, pressure is 0.8MPa, 150 DEG C solidify after at 900 DEG C cracking resin, finally at 1500 DEG C, carry out the infiltration of liquid silicon, obtain C/SiC sharp-pointed leading edge.
Claims (6)
1. a sharp-pointed leading edge preparation method for the coated two-dimension laminate carbon fiber protective layer of fiber preform core surface, is characterized in that step is as follows:
Step 1, making mould: the design paper according to sharp-pointed leading edge member is made formpiston and former, between formpiston and former, leaves space; Described former internal surface radius curved surface coincide with the leading-edge radius curved surface of sharp-pointed leading edge member;
Step 2, prepare two-dimension laminate carbon fiber protective layer: lamination carbon cloth is laid in to male mold surfaces, adopts fiber that carbon cloth is firmly sewed up fixing by position, hole reserved on mould; Adopt CVI process deposits RESEARCH OF PYROCARBON and SiC, fix protective layer shape, after the demoulding, obtain the housing of two-dimension laminate carbon fiber protective layer;
The thickness of described lamination carbon cloth is die clearance thickness;
Step 3, prepare fiber preform inner core:
Adopt CVI densifying method to prepare carbon-fiber reinforced carbon C/C or carbon fibre reinforced silicon carbide C/SiC precast body, its density is controlled at 1.2g/cm
3-1.8g/cm
3scope, carries out mechanical workout by the inner core size of sharp-pointed leading edge member to precast body, obtains sharp-pointed leading edge fiber preform inner core;
Step 4, group two-dimension laminate carbon fiber protective layer and fiber preform inner core close: in housing and the punching of inner core corresponding position, adopt C/SiC pin by housing and inner core combination, obtain sharp-pointed leading edge precast body;
Step 5, prepare sharp-pointed leading edge: adopt CVI technique to the further densification of sharp-pointed leading edge precast body, obtain the sharp-pointed leading edge of final matrix material.
2. the sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of fiber preform core surface according to claim 1, is characterized in that: with the preparation of CVI carbon-fiber reinforced carbon C/C or the carbon fibre reinforced silicon carbide C/SiC precast body of PIP densifying method step of replacing 3.
3. the sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of fiber preform core surface according to claim 1, is characterized in that: with the further densification process of the sharp-pointed leading edge precast body of CVI of PIP or RMI technique step of replacing 5.
4. the sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of fiber preform core surface according to claim 1, is characterized in that: the space between described formpiston and former is 1～2mm.
5. the sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of fiber preform core surface according to claim 1, is characterized in that: described moulding stock is graphite material.
6. the sharp-pointed leading edge preparation method of the coated two-dimension laminate carbon fiber protective layer of fiber preform core surface according to claim 1, is characterized in that: described former thickness is 5～10mm; Described formpiston size is identical with precast body inner core.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105835455A (en) * | 2015-12-15 | 2016-08-10 | 西安鑫垚陶瓷复合材料有限公司 | 2D carbon/silicon-silicon carbide composite material pin preparation method and preparation method and structure of 2D carbon/silicon-silicon carbide composite material pin preform |
| CN108218453A (en) * | 2017-12-01 | 2018-06-29 | 中国航空工业集团公司基础技术研究院 | A kind of forming method of thin-walled circular cone cylinder-shaped ceramic based composite material component |
| CN110549643A (en) * | 2019-09-06 | 2019-12-10 | 长沙晶优新材料科技有限公司 | antenna cover plate profiling prefabricated part puncturing method and antenna cover plate forming method |
| CN113603495A (en) * | 2021-07-29 | 2021-11-05 | 西北工业大学 | Method for preparing ceramic matrix composite bolt and pin based on long rod-shaped prefabricated body structure |
| CN113816755A (en) * | 2021-10-14 | 2021-12-21 | 西安鑫垚陶瓷复合材料有限公司 | Two-dimensional silicon carbide/silicon carbide composite material bar and connecting piece preparation method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020002405A1 (en) * | 2000-03-15 | 2002-01-03 | Hilmar Janusson | Apparatus and process for making prosthetic suction sleeve |
| CN102834220A (en) * | 2010-03-19 | 2012-12-19 | 斯奈克玛 | Method for producing metal insert to protect leading edge made of composite material |
| CN102889185A (en) * | 2012-10-22 | 2013-01-23 | 保定华翼风电叶片研究开发有限公司 | Wind turbine blade for wind driven generator and machining process thereof |
| CN103042701A (en) * | 2012-12-27 | 2013-04-17 | 中国科学院工程热物理研究所 | Integrated formation device and method for wind power blade |
| CN103072287A (en) * | 2013-01-06 | 2013-05-01 | 宁波锦浪新能源科技有限公司 | Manufacturing process of fan blade employing fiber-reinforced resin matrix composite and used for wind-driven generator |
-
2014
- 2014-03-26 CN CN201410116151.3A patent/CN103936450B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020002405A1 (en) * | 2000-03-15 | 2002-01-03 | Hilmar Janusson | Apparatus and process for making prosthetic suction sleeve |
| CN102834220A (en) * | 2010-03-19 | 2012-12-19 | 斯奈克玛 | Method for producing metal insert to protect leading edge made of composite material |
| CN102889185A (en) * | 2012-10-22 | 2013-01-23 | 保定华翼风电叶片研究开发有限公司 | Wind turbine blade for wind driven generator and machining process thereof |
| CN103042701A (en) * | 2012-12-27 | 2013-04-17 | 中国科学院工程热物理研究所 | Integrated formation device and method for wind power blade |
| CN103072287A (en) * | 2013-01-06 | 2013-05-01 | 宁波锦浪新能源科技有限公司 | Manufacturing process of fan blade employing fiber-reinforced resin matrix composite and used for wind-driven generator |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105835455A (en) * | 2015-12-15 | 2016-08-10 | 西安鑫垚陶瓷复合材料有限公司 | 2D carbon/silicon-silicon carbide composite material pin preparation method and preparation method and structure of 2D carbon/silicon-silicon carbide composite material pin preform |
| CN108218453A (en) * | 2017-12-01 | 2018-06-29 | 中国航空工业集团公司基础技术研究院 | A kind of forming method of thin-walled circular cone cylinder-shaped ceramic based composite material component |
| CN108218453B (en) * | 2017-12-01 | 2021-03-26 | 中国航空工业集团公司基础技术研究院 | Forming method of thin-wall conical cylindrical ceramic matrix composite component |
| CN110549643A (en) * | 2019-09-06 | 2019-12-10 | 长沙晶优新材料科技有限公司 | antenna cover plate profiling prefabricated part puncturing method and antenna cover plate forming method |
| CN110549643B (en) * | 2019-09-06 | 2021-09-07 | 长沙晶优新材料科技有限公司 | Antenna cover plate profiling prefabricated part puncturing method and antenna cover plate forming method |
| CN113603495A (en) * | 2021-07-29 | 2021-11-05 | 西北工业大学 | Method for preparing ceramic matrix composite bolt and pin based on long rod-shaped prefabricated body structure |
| CN113816755A (en) * | 2021-10-14 | 2021-12-21 | 西安鑫垚陶瓷复合材料有限公司 | Two-dimensional silicon carbide/silicon carbide composite material bar and connecting piece preparation method |
| CN113816755B (en) * | 2021-10-14 | 2023-09-01 | 西安鑫垚陶瓷复合材料有限公司 | Two-dimensional silicon carbide/silicon carbide composite bar and preparation method of connecting piece |
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