Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
C23C-016/00
출원번호
US-0784734
(2004-02-23)
등록번호
US-7306826
(2007-12-11)
발명자
/ 주소
Subramanian,Suresh
Steibel,James Dale
Carper,Douglas Melton
Flandermeyer,Brian Keith
출원인 / 주소
General Electric Company
대리인 / 주소
McNees Wallace & Nurick LLC
인용정보
피인용 횟수 :
10인용 특허 :
18
초록▼
A method for making a ceramic matrix composite turbine engine component, wherein the method includes providing a plurality of biased ceramic plies, wherein each biased ply comprises ceramic fiber tows, the tows being woven in a first warp direction and a second weft direction, the second weft direct
A method for making a ceramic matrix composite turbine engine component, wherein the method includes providing a plurality of biased ceramic plies, wherein each biased ply comprises ceramic fiber tows, the tows being woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction. The plurality of biased plies are laid up in a preselected arrangement to form the component, and a preselected number of the plurality of biased plies are oriented such that the orientation of the first warp direction of the plies lie about in the direction of maximum tensile stress during normal engine operation. A coating is applied to the plurality of biased plies. The coated component preform is then densified.
대표청구항▼
What is claimed is: 1. A method of manufacturing a rotatable turbine engine component, the component having a direction of maximum tensile stress during normal engine operation, comprising the steps of: providing a plurality of biased ceramic plies, each biased ply comprising ceramic fiber tows, th
What is claimed is: 1. A method of manufacturing a rotatable turbine engine component, the component having a direction of maximum tensile stress during normal engine operation, comprising the steps of: providing a plurality of biased ceramic plies, each biased ply comprising ceramic fiber tows, the tows woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction, and wherein a number of tows in the second weft direction allows the biased plies to maintain their structural integrity when handled; laying up the plurality of biased plies in a preselected arrangement to form a rotatable component shape, wherein a preselected number of the plurality of biased plies are oriented such that the orientation of the first warp direction of a preselected number of the plurality of biased plies lie about in the direction of maximum tensile stress during normal engine operation, wherein normal engine operation includes rotation of the rotatable turbine engine component; rigidizing the component shape with a layer of BN and a layer of SiC to form a coated component preform using chemical vapor infiltration; partially densifying the coated component preform using carbon-containing slurry; and further densifying the coated component preform with at least silicon to form a rotatable ceramic matrix composite aircraft engine component with biased architecture. 2. The method of claim 1, wherein a ratio of a number of tows in the first warp direction to the number of tows in the second weft direction is at least about 2:1. 3. The method of claim 1, wherein the plies are silicon carbide containing plies. 4. The method of claim 2, wherein the turbine engine component is a turbine blade. 5. The method of claim 2, wherein the turbine engine component is a cooled turbine nozzle. 6. The method of claim 2, wherein the turbine engine component is an uncooled turbine nozzle. 7. A method of manufacturing a rotatable ceramic matrix composite aircraft engine component, the component having a direction of maximum tensile stress during normal engine operation, comprising the steps of: providing a plurality of prepreg ceramic plies, the plies comprising prepreg ceramic fiber tows, the tows in each ply lying adjacent to one another in a planar arrangement such that each ply has a unidirectional orientation; laying up the plurality of prepreg ceramic cloth plies in a preselected arrangement to form a rotatable turbine blade shape such that a preselected number of outermost plies are oriented at about 0째 with respect to the direction of maximum tensile stress of the turbine engine component during normal engine operations wherein normal engine operation includes rotation of the rotatatable turbine engine component; heating the turbine blade shape to form a ceramic preform; and densifying the turbine blade preform with at least silicon to form a rotatable ceramic matrix composite turbine blade.
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이 특허에 인용된 특허 (18)
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Pak Sung S. ; Goettler Richard W. ; Tolley Archie N., Continuous deposition of bridge free interfacial coatings on multifilamentary ceramic fiber tows.
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