CN103936450B - Preparation method for sharp leading edge - Google Patents
Preparation method for sharp leading edge Download PDFInfo
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- CN103936450B CN103936450B CN201410116151.3A CN201410116151A CN103936450B CN 103936450 B CN103936450 B CN 103936450B CN 201410116151 A CN201410116151 A CN 201410116151A CN 103936450 B CN103936450 B CN 103936450B
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- leading edge
- sharp leading
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- protective layer
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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 leading edge preparation method of a kind of fiber preform core surface coated two-dimension laminate carbon fiber protective layer, the antiscour that prepared by improving, matrix material sharp leading edge is on active service in high temperature environments degrades performance.
Background technology
Continuous fibre toughened silicon carbide composite material (C/SiC) is a kind of desirable high-temperature structural material, has high temperature resistant, the series of advantages such as low density, high strength, anti-thermal shock, has wide practical use in Aeronautics and Astronautics field.By matrix modification, introduce different high-temperature-phases, the high temperature anti-yaw damper performance of C/SiC can be improved greatly, improve its service life under harsh Aerodynamic Heating environment and quality.
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 meet the preparation requirement of sharp leading edge precast body very well, especially to small curvature radius leading edge (<3mm), is difficult to the radius curved surface of perfect braiding sharp leading edge precast body; If obtain radius curved surface through suitable mechanical workout, cutting or polishing, leading-edge radius position can be caused to occur fibre breakage and fall pin situation, form small projection and pit in leading edge surface.0.5 power of the heat flow density that Aerodynamic Heating produces and stationary point radius is 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.
When sharp leading edge prepares protective layer; be difficult to braiding sharp leading edge according to common braiding structure, leading edge surface there will be fibre breakage and falls pin situation when machine-shaping, form small projection and pit in leading edge surface; cause huge hot-fluid to concentrate in Aerodynamic Heating, cause serious ablation.
Summary of the invention
The technical problem solved
In order to avoid the deficiencies in the prior art part; the present invention proposes the sharp leading edge preparation method of a kind of fiber preform core surface coated two-dimension laminate carbon fiber protective layer; 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 the local heat flux falling pin and cause concentrates, the antiscour improving the matrix material sharp leading edge of preparation degrades performance.
Technical scheme
A sharp leading edge preparation method for fiber preform core surface coated two-dimension laminate carbon fiber protective layer, is characterized in that step is as follows:
Step 1, making mould: the design paper according to sharp leading edge component makes formpiston and former, leaves space between formpiston and former; The leading-edge radius curved surface of described former internal surface radius curved surface and sharp leading edge component coincide;
Step 2, prepare two-dimension laminate carbon fiber protective layer: lamination carbon cloth is laid in male mold surfaces, adopt fiber firmly to be sewed up by carbon cloth fixing by position, hole reserved on mould; Adopt CVI process deposits RESEARCH OF PYROCARBON and SiC, fixing protective layer shape, obtains the housing of two-dimension laminate carbon fiber protective layer after the demoulding;
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 domination is at 1.2g/cm
3-1.8g/cm
3scope, carries out mechanical workout by the inner core size of sharp leading edge component to precast body, obtains sharp leading edge fiber preform inner core;
Step 4, group two-dimension laminate carbon fiber protective layer and fiber preform inner core close: punch at housing and inner core corresponding position, adopt C/SiC pin housing and inner core to be combined, obtain sharp leading edge precast body;
Step 5, prepare sharp leading edge: adopt CVI technique to the further densification of sharp leading edge precast body, obtain final matrix material sharp leading edge.
With the preparation of the CVI carbon-fiber reinforced carbon C/C of PIP densifying method step of replacing 3 or carbon fibre reinforced silicon carbide C/SiC precast body.
With the further densification process of CVI sharp leading edge precast body 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 leading edge preparation method of a kind of fiber preform core surface coated two-dimension laminate carbon fiber protective layer 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 the local heat flux falling pin and cause concentrates, the antiscour improving the matrix material sharp leading edge of preparation degrades performance.Due at fiber preform core surface coated two-dimension laminate carbon fiber protective layer; make protective layer fit tightly through processing precast body inner core; protective layer is without the need to carrying out mechanical workout; surface is complete; without small projection and pit; using it as the radius surface of sharp leading edge, that can eliminate precast body inner core falls pin and fibre breakage to the impact of Aerodynamic Heating, makes the matrix material sharp leading edge of preparation have good antiscour to degrade performance.
Accompanying drawing explanation
Fig. 1 graphite jig photo.
Fig. 2 protective layer photo.
Sharp leading edge precast body full face prepared by Fig. 3.
Sharp leading edge precast body side photo prepared by Fig. 4.
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 D refraction statics C/SiC, and preparation process is as follows:
Prepared by mould: adopt graphite material, and 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, is uniformly distributed under distance leading-edge radius top 15mm.
Prepared by two-dimension laminate protective layer: smooth for 5 layers of carbon cloth is laid on male mold surfaces, is firmly sewed up by carbon cloth fixing by Kong Weiyong fiber reserved on mould.Adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is loaded into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, obtains shaping protective layer housing.Cut into the demoulding of wide 25mm block after being polished by stitching carbon fiber, obtain 2D-C/SiC protective layer housing.
Prepared by fiber preform inner core: be 1.7g/cm by density
3d refraction statics 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, adopts C/SiC pin housing and inner core to be combined, obtains leading edge precast body.
Prepared by sharp leading edge: adopt VPI in conjunction with RMI method, vacuum pressure infiltration resol slurry in precast body, vacuum tightness is-0.08MPa, and pressure is 0.8MPa, after 150 DEG C of solidifications, at 900 DEG C, cracking resin finally infiltrates silicon-zirconium at 1700 DEG C, obtains C/SiC-ZrC sharp 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:
Prepared by mould: adopt graphite material, and 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, is uniformly distributed under distance leading-edge radius top 15mm.
Prepared by two-dimension laminate protective layer: smooth for 5 layers of carbon cloth is laid on male mold surfaces, is firmly sewed up by carbon cloth fixing by Kong Weiyong fiber reserved on mould.Adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is loaded into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, obtains shaping protective layer housing.Cut into the demoulding after wide 25mm block after being polished by stitching carbon fiber, obtain 2D-C/SiC protective layer housing.
Prepared by fiber preform inner core: be 1.7g/cm by density
3d refraction statics 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, adopts C/SiC pin housing and inner core to be combined, obtains leading edge precast body.
Prepared by sharp leading edge: adopt CVI method, utilize hydrogen that MTS is loaded into cvd furnace, and at 1000 DEG C, cracking MTS under 5KPa pressure, depositing silicon silicon substrate in leading edge precast body, obtains C/SiC sharp leading edge.
Embodiment 3:
Leading-edge radius is 1.5mm, and inner core material is the C/SiC sharp leading edge of 3 dimension puncture C/SiC, and preparation process is as follows:
Prepared by mould: adopt graphite material, and 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, is uniformly distributed under distance leading-edge radius top 15mm.
Prepared by two-dimension laminate protective layer: smooth for 5 layers of carbon cloth is laid on male mold surfaces, is firmly sewed up by carbon cloth fixing by Kong Weiyong fiber reserved on mould.Adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is loaded into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, obtains shaping protective layer housing.Cut into the demoulding after wide 25mm block after being polished by stitching carbon fiber, obtain 2D-C/SiC protective layer housing.
Prepared by fiber preform inner core: be 1.7g/cm by density
3d refraction statics 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, adopts C/SiC pin housing and inner core to be combined, obtains leading edge precast body.
Prepared by sharp leading edge: 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, after 150 DEG C of solidifications at 900 DEG C cracking resin, finally at 1500 DEG C, carry out the infiltration of liquid silicon, obtain C/SiC sharp leading edge.
Claims (6)
1. a sharp leading edge preparation method for fiber preform core surface coated two-dimension laminate carbon fiber protective layer, is characterized in that step is as follows:
Step 1, making mould: the design paper according to sharp leading edge component makes formpiston and former, leaves space between formpiston and former; The leading-edge radius curved surface of described former internal surface radius curved surface and sharp leading edge component coincide;
Step 2, prepare two-dimension laminate carbon fiber protective layer: lamination carbon cloth is laid in male mold surfaces, adopt fiber firmly to be sewed up by carbon cloth fixing by position, hole reserved on mould; Adopt CVI process deposits RESEARCH OF PYROCARBON and SiC, fixing protective layer shape, obtains the housing of two-dimension laminate carbon fiber protective layer after the demoulding;
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 domination is at 1.2g/cm
3-1.8g/cm
3scope, carries out mechanical workout by the inner core size of sharp leading edge component to precast body, obtains sharp leading edge fiber preform inner core;
Step 4, combined two-dimension lamination carbon fiber protective layer and fiber preform inner core: punch at housing and inner core corresponding position, adopt C/SiC pin housing and inner core to be combined, obtain sharp leading edge precast body;
Step 5, prepare sharp leading edge: adopt CVI technique to the further densification of sharp leading edge precast body, obtain final matrix material sharp leading edge.
2. the sharp leading edge preparation method of fiber preform core surface coated two-dimension laminate carbon fiber protective layer according to claim 1, is characterized in that: with the preparation of the CVI carbon-fiber reinforced carbon C/C of PIP densifying method step of replacing 3 or carbon fibre reinforced silicon carbide C/SiC precast body.
3. the sharp leading edge preparation method of fiber preform core surface coated two-dimension laminate carbon fiber protective layer according to claim 1, is characterized in that: with the further densification process of CVI sharp leading edge precast body of PIP or RMI technique step of replacing 5.
4. the sharp leading edge preparation method of fiber preform core surface coated two-dimension laminate carbon fiber protective layer according to claim 1, is characterized in that: the space between described formpiston and former is 1 ~ 2mm.
5. the sharp leading edge preparation method of fiber preform core surface coated two-dimension laminate carbon fiber protective layer according to claim 1, is characterized in that: described moulding stock is graphite material.
6. the sharp leading edge preparation method of fiber preform core surface coated two-dimension laminate carbon fiber protective layer 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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| CN105835455B (en) * | 2015-12-15 | 2019-05-10 | 西安鑫垚陶瓷复合材料有限公司 | Two-dimensional Carbon/silico-carbo SiClx composite material pin preparation method |
| 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 |
| 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 |
| 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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| 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 |
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| ATE456340T1 (en) * | 2000-03-15 | 2010-02-15 | Ossur Hf | APPARATUS AND METHOD FOR PRODUCING A PROSTHETIC SUCTION CUFF |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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