CN103601523A - Needled preform structure of ceramic matrix composite pin and manufacturing method of pin by adopting structure - Google Patents
Needled preform structure of ceramic matrix composite pin and manufacturing method of pin by adopting structure Download PDFInfo
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- CN103601523A CN103601523A CN201310556795.XA CN201310556795A CN103601523A CN 103601523 A CN103601523 A CN 103601523A CN 201310556795 A CN201310556795 A CN 201310556795A CN 103601523 A CN103601523 A CN 103601523A
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- needling
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- latitude cloth
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Abstract
The invention relates to a needled preform structure of a ceramic matrix composite pin and a manufacturing method of the pin by using the structure. The needled preform structure is a needled structure formed by alternately layering long-fiber weft-less fabrics and short-fiber meshed tires, wherein the number of layers of the weft-less fabrics in which an included angle between the long fiber direction and the axial direction of the pin ranges from 5 degree below zero to 5 degrees is 3-9 times that of the number of layers of the weft-less fabrics in which an included angle between the long fiber direction and the axial direction of the pin ranges from 85 degree to 95 degrees. The manufacturing method comprises the following steps: performing pyrolytic carbon deposition on the needled preform structure by adopting a chemical vapor infiltration process, performing silicon carbide deposition by adopting the chemical vapor infiltration process, and finally, machining the densified preform into the pin by adopting a machining mode. The low-cost needled preform pin has the shear strength level of high-cost preform (three-dimensional four-way braiding, three-dimensional five-way braiding or three-way orthogonal preform) pins in the prior art, and can be used for manufacturing complex members of ceramic matrix composite materials with high connection strength.
Description
Technical field
The invention belongs to technical field of composite materials, the precursor structure that relates to a kind of ceramic matric composite, be particularly related to a kind of precursor structure of the ceramic matric composite pin connecting for ceramic matric composite, and the preparation method of this ceramic matric composite pin.
Background technology
Ceramic matric composite pin interconnection technique is a kind of important technology of preparing ceramic matric composite complex component.The ceramic matric composite pin of high shear strength is one of key guaranteeing high strength of joint.Adopt three-dimensional four-way braiding that fiber volume fraction is high, three-dimensional five to braiding or three-dimensional quadrature precast body as pin precast body, can effectively improve the shear strength of matrix material pin, but the preparation difficulty of this two classes precast body is large, cost is high.
Summary of the invention
The precursor structure that the object of this invention is to provide a kind of ceramic matric composite pin, and then the preparation method who utilizes this precursor structure to prepare ceramic matric composite pin is provided, make needling preform pin cheaply there is the shearing resistance level of expensive precast body of the prior art (three-dimensional four-way braiding, three-dimensional five is to braiding or three-dimensional quadrature precast body) pin.
The technical solution used in the present invention is as follows:
A needling preform structure for ceramic matric composite pin, for macrofiber replaces the needling structure of laying without latitude cloth and web of staple fibers tire; Its medium staple fibre direction and the axial angle of pin be-5 °～5 ° without the latitude cloth number of plies be macrofiber direction and the axial angle of pin be 85 °～95 ° the 3-9 without the latitude cloth number of plies doubly.
Further, describedly without the macrofiber in latitude cloth, adopt identical or differing materials with staple fibre in described net tire.
Further, described without being the macrofiber of-5 °～5 ° with the axial angle of pin in latitude cloth and adopting identical or differing materials with the macrofiber that the axial angle of pin is 85 °～95 °.
Further, the needling density of above-mentioned needling preform structure is 25～30 pins/cm
2.
Further, described long stapled length is the whole length without latitude cloth (can be considered endless), and the length of the staple fibre that net tire is used is 65～70mm.
Further, the described area density without latitude cloth is 160～170g/m
2, thickness is 0.4～0.55mm; Area density 20～the 30g/m of described net tire
2, thickness is 0.1～0.15mm.
Adopt above-mentioned needling preform structure to prepare a method for ceramic matric composite pin, its step comprises:
1) take propane as reaction gas, nitrogen is carrier gas, adopts chemical vapor infiltration technique needling preform structure described in claim 1 to be carried out to the deposition of RESEARCH OF PYROCARBON;
2) take trichloromethyl silane as reaction raw materials, adopt chemical vapor infiltration technique to carry out the deposition of silicon carbide;
3) adopting mach mode by step 2) precast body after the densification that makes is processed into pin.
Further, in step 1), the flow of propane is 1.2 ± 0.1l/h, and the flow of nitrogen is 0.8 ± 0.05l/h, and depositing temperature is 1020 ± 10 ℃, and deposition pressure is 2 ± 1Kpa, and depositing time is 200 ± 20 hours.
Further, step 2) employing hydrogen is carrier gas, in the mode of bubbling, brings trichloromethyl silane into pyroreaction chamber, and the consumption of trichloromethyl silane is 150 ± 5g/h; Employing argon gas is carrier gas, and flow is 1.0 ± 0.1l/h.
Further, step 2) depositing temperature is 1050 ± 10 ℃, and deposition pressure is 2 ± 1Kpa, and depositing time is 400 ± 20 hours.
Needling preform structure for the preparation of ceramic matric composite pin of the present invention, improved and be parallel to the long stapled content of the axial carrying of pin, made the low needling preform of cost of preparation can reach the reinforced effects of existing high preparation cost precast body equally.The ceramic matric composite pin that utilizes this precursor structure to prepare, can be used for preparing the ceramic matric composite complex component of high strength of joint.
Accompanying drawing explanation
Fig. 1 is pin needling preform structure medium staple fibre direction of the present invention and the transversal relation of plane schematic diagram of pin.
Fig. 2 is without two macrofiber direction schematic diagram of latitude cloth in embodiment 1.
Fig. 3 is the photo of the ceramic matric composite pin that makes in embodiment 1.
Fig. 4 is without two macrofiber direction schematic diagram of latitude cloth in embodiment 2.
Fig. 5 is without two macrofiber direction schematic diagram of latitude cloth in embodiment 3.
Fig. 6 is the flow chart of steps of preparing C/C-SiC matrix material pin in embodiment.
Embodiment
Below by specific embodiments and the drawings, the present invention will be further described.
The needling preform structure of ceramic matric composite pin of the present invention is that macrofiber replaces the needling structure of laying without latitude cloth and web of staple fibers tire, and its medium staple fibre direction is macrofiber direction perpendicular to the axial 3-9 without the latitude cloth number of plies of pin doubly along pin axial direction due without the latitude cloth number of plies.Fig. 1 is pin needling preform structure medium staple fibre direction of the present invention and the transversal relation of plane schematic diagram of pin.Wherein, circle indicate without the direction of latitude cloth medium staple fibre along pin axially (with the axial angle of pin be-5 °～5 °), straight line indicate without the direction of latitude cloth medium staple fibre along perpendicular to the axial direction of pin (with the axial angle of pin be 85 °～95 °).Below by specific examples, describe.
Embodiment 1:
The precursor structure of the present embodiment is that one deck macrofiber replaces the needling structure of laying without latitude cloth and one deck web of staple fibers tire; Every three layers of macrofiber direction and the axial angle of pin be-5 ° without after latitude cloth/net tire laying, carry out one deck macrofiber direction with the axial angle of pin be 85 ° without latitude cloth/net tire laying, as shown in Figure 2, be respectively macrofiber direction 1 and macrofiber direction 2; In needling preform, fiber used is T70012K carbon fiber.
Other parameter of this precursor structure is: needling density 25 pins/cm
2; Net tire staple length used is 65mm; Without latitude cloth area density 160g/m
2, thickness 0.4mm; Net tyre surface density 20g/m
2, thickness 0.1mm.
Then, adopt above-mentioned precursor structure to prepare C/C-SiC matrix material pin, concrete steps comprise:
1) adopt chemical vapor infiltration (CVI) technique precast body to be carried out to the deposition of RESEARCH OF PYROCARBON: take propane as reaction gas, flow is 1.2l/h; Nitrogen is carrier gas, and flow is 0.8l/h; 1020 ℃ of depositing temperatures; Deposition pressure 2Kpa; Depositing time 200 hours.
2) adopt chemical vapor infiltration (CVI) technique to carry out the deposition of silicon carbide (SiC): the trichloromethyl silane (MTS) of take is reaction raw materials, hydrogen is carrier gas, mode with bubbling is brought MTS into pyroreaction chamber, the consumption of MTS is 150g/h, argon gas is carrier gas, and flow is 1.0l/h, 1050 ℃ of depositing temperatures, deposition pressure 2Kpa, depositing time 400 hours.
3) mode that employing machine adds is processed into the precast body after densification the pin of diameter 6mm.Fig. 3 is the pin photo making.
The shear strength of C/C-SiC matrix material pin prepared by the precursor structure of employing the present embodiment is 81MPa.
Embodiment 2:
The precursor structure of the present embodiment is the needling structure that one deck carbon fiber-free weft fabric and one deck carbon fibre web tire replace laying; After every six layers of macrofiber direction and pin axial clamp are T3006K carbon fiber-free weft fabric/T70012K carbon fibre web tire laying at 0 °, angle, carry out one deck and the axial angle of macrofiber direction pin and be T70012K carbon fiber-free weft fabric/T70012K carbon fibre web tire laying of 90 °.As shown in Figure 4, above-mentioned both direction is respectively macrofiber direction 1 and macrofiber direction 2.
Other parameter of above-mentioned precursor structure is: needling density 30 pins/cm
2; Net tire staple length used is 70mm; Without latitude cloth area density 170g/m
2, thickness 0.55mm; Net tyre surface density 30g/m
2, thickness 0.15mm.
Then, adopt above-mentioned precursor structure to prepare C/C-SiC matrix material pin, concrete steps comprise:
1) adopt CVI technique precast body to be carried out to the deposition of RESEARCH OF PYROCARBON, take propane as reaction gas, flow is 1.1l/h, and nitrogen is carrier gas, and flow is 0.75l/h, 1010 ℃ of depositing temperatures, deposition pressure 1Kpa, depositing time 180 hours.
2) adopt CVI technique to carry out the deposition of SiC, take MTS as reaction raw materials, hydrogen is carrier gas, in the mode of bubbling, brings MTS into pyroreaction chamber, the consumption of MTS is 145g/h, and argon gas is carrier gas, and flow is 0.9l/h, 1040 ℃ of depositing temperatures, deposition pressure 1Kpa, depositing time 380 hours.
3) mode that employing machine adds is processed into the precast body after densification the pin of diameter 6mm.
The shear strength of C/C-SiC matrix material pin prepared by the precursor structure of employing the present embodiment is 96MPa.
Embodiment 3:
The precursor structure of the present embodiment is that one deck macrofiber replaces the needling structure of laying without latitude cloth and one deck web of staple fibers tire; Every nine layers of macrofiber direction and the axial angle of pin be 5 ° without after latitude cloth/net tire laying, carry out the axial angle of one deck macrofiber direction and pin and be 95 ° without latitude cloth/net tire laying, as shown in Figure 5, above-mentioned both direction is respectively macrofiber direction 1 and macrofiber direction 2.; In needling preform, fiber used is T70012K carbon fiber.
Other parameter of above-mentioned precursor structure is: needling density 25 pins/cm
2; Net tire staple length used is 65mm; Without latitude cloth area density 160g/m
2, thickness 0.55mm; Net tyre surface density 25g/m
2, thickness 0.15mm.
Then, adopt above-mentioned precursor structure to prepare C/C-SiC matrix material pin, concrete steps flow process as shown in Figure 6, comprising:
1) adopt CVI technique precast body to be carried out to the deposition of RESEARCH OF PYROCARBON, take propane as reaction gas, flow is 1.3l/h, and nitrogen is carrier gas, and flow is 0.85l/h, 1030 ℃ of depositing temperatures, deposition pressure 3Kpa, depositing time 220 hours.
2) adopt CVI technique to carry out the deposition of SiC, take MTS as reaction raw materials, hydrogen is carrier gas, in the mode of bubbling, brings MTS into pyroreaction chamber, the consumption of MTS is 155g/h, and argon gas is carrier gas, and flow is 1.1l/h, 1060 ℃ of depositing temperatures, deposition pressure 3Kpa, depositing time 420 hours.
3) mode that employing machine adds is processed into the precast body after densification the pin of diameter 6mm.
The shear strength of C/C-SiC matrix material pin prepared by the precursor structure of employing the present embodiment is 105MPa.
The shear strength contrast list that table 1 is the matrix material pin that in embodiments of the invention 1-3 and prior art, different methods makes.Can find out, the pin of ceramic matric composite cheaply that adopts needling preform structure of the present invention to make, can reach the reinforced effects of existing high preparation cost precast body, the pin that wherein shear strength of the pin of embodiment 3 preparations is even prepared than existing method is taller.
The shear strength of the different precursor structure C/C-SiC matrix material of table 1. pin (diameter 6mm)
Although disclose for the purpose of illustration specific embodiments of the invention and accompanying drawing, its object is help to understand content of the present invention and implement according to this, but it will be appreciated by those skilled in the art that: without departing from the spirit and scope of the invention and the appended claims, various replacements, variation and modification are all possible.The present invention should not be limited to this specification sheets most preferred embodiment and the disclosed content of accompanying drawing, and the scope that the scope of protection of present invention defines with claims is as the criterion.
Claims (10)
1. the needling preform structure of a ceramic matric composite pin, it is characterized in that, that macrofiber replaces the needling structure of laying without latitude cloth and web of staple fibers tire, described macrofiber without latitude cloth medium staple fibre direction and the axial angle of pin be-5 °～5 ° without the latitude cloth number of plies be macrofiber direction and the axial angle of pin be 85 °～95 ° without 3～9 times of the latitude cloth number of plies.
2. the needling preform structure of ceramic matric composite pin as claimed in claim 1, is characterized in that: describedly without the macrofiber in latitude cloth, adopt identical or differing materials with the staple fibre in described net tire.
3. the needling preform structure of ceramic matric composite pin as claimed in claim 1, is characterized in that: described without being the macrofiber of-5 °～5 ° with the axial angle of pin in latitude cloth and adopting identical or differing materials with the macrofiber that the axial angle of pin is 85 °～95 °.
4. the needling preform structure of ceramic matric composite pin as claimed in claim 1, is characterized in that: the needling density of described needling structure is 25～30 pins/cm
2.
5. the needling preform structure of ceramic matric composite pin as claimed in claim 1, is characterized in that: described long stapled length is the whole length without latitude cloth, and the length of described staple fibre is 65～70mm.
6. the needling preform structure of ceramic matric composite pin as claimed in claim 1, is characterized in that: the described area density without latitude cloth is 160～170g/m
2, thickness is 0.4～0.55mm; Area density 20～the 30g/m of described net tire
2, thickness is 0.1～0.15mm.
7. adopt needling preform structure described in claim 1 to prepare a method for ceramic matric composite pin, its step comprises:
1) take propane as reaction gas, nitrogen is carrier gas, adopts chemical vapor infiltration technique needling preform structure described in claim 1 to be carried out to the deposition of RESEARCH OF PYROCARBON;
2) take trichloromethyl silane as reaction raw materials, adopt chemical vapor infiltration technique to carry out the deposition of silicon carbide;
3) adopting mach mode by step 2) precast body after the densification that makes is processed into pin.
8. method as claimed in claim 7, is characterized in that: in step 1), the flow of propane is 1.2 ± 0.1l/h, and the flow of nitrogen is 0.8 ± 0.05l/h, and depositing temperature is 1020 ± 10 ℃, and deposition pressure is 2 ± 1Kpa, and depositing time is 200 ± 20 hours.
9. method as claimed in claim 7, is characterized in that: step 2) employing hydrogen is carrier gas, in the mode of bubbling, brings trichloromethyl silane into pyroreaction chamber, the consumption of trichloromethyl silane is 150 ± 5g/h; Employing argon gas is carrier gas, and flow is 1.0 ± 0.1l/h.
10. method as claimed in claim 9, is characterized in that: step 2) depositing temperature be 1050 ± 10 ℃, deposition pressure is 2 ± 1Kpa, depositing time is 400 ± 20 hours.
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| CN201310556795.XA CN103601523B (en) | 2013-11-11 | 2013-11-11 | A kind of needling preform structure of ceramic matric composite pin and preparation method |
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Cited By (2)
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| CN104711774A (en) * | 2015-03-31 | 2015-06-17 | 赵晓明 | Full-carbon-fiber weftless cloth containing carbon-fiber filaments in positive and negative 45-degree directions and preparation method thereof |
| CN110005481A (en) * | 2017-11-13 | 2019-07-12 | 通用电气公司 | Use the CMC component and production of mechanical splice |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104711774A (en) * | 2015-03-31 | 2015-06-17 | 赵晓明 | Full-carbon-fiber weftless cloth containing carbon-fiber filaments in positive and negative 45-degree directions and preparation method thereof |
| CN110005481A (en) * | 2017-11-13 | 2019-07-12 | 通用电气公司 | Use the CMC component and production of mechanical splice |
| US11802486B2 (en) | 2017-11-13 | 2023-10-31 | General Electric Company | CMC component and fabrication using mechanical joints |
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