Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-009/02
F01D-005/12
F01D-025/12
F01D-025/08
출원번호
UP-0155786
(2005-06-17)
등록번호
US-7549840
(2009-07-01)
발명자
/ 주소
Subramanian, Suresh
Steibel, James Dale
Carper, Douglas Melton
출원인 / 주소
General Electric Company
대리인 / 주소
McNees Wallace & Nurick, LLC
인용정보
피인용 횟수 :
5인용 특허 :
26
초록▼
A method of manufacturing a turbine engine component comprising the steps of providing and laying up a plurality of ceramic plies comprising woven ceramic fiber tows to form a turbine engine component shape, inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such t
A method of manufacturing a turbine engine component comprising the steps of providing and laying up a plurality of ceramic plies comprising woven ceramic fiber tows to form a turbine engine component shape, inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such that each fugitive fiber tow passes through a preselected number of ceramic plies, burning off the fugitive fiber tows, the burning producing through-thickness void regions, rigidizing the component shape with a layer of BN and a layer of SiC to form a coated component preform using chemical vapor infiltration, and partially densifying the coated component preform using carbon-containing slurry and filling the through thickness void regions, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component with in-situ ceramic matrix plugs formed where the through-thickness void regions were located.
대표청구항▼
What is claimed is: 1. A method of manufacturing a turbine engine component comprising the steps of: providing a plurality of ceramic plies, each ply comprising woven ceramic fiber tows; providing a plurality of fugitive fibers tows; laying up the plurality of plies in a preselected arrangement to
What is claimed is: 1. A method of manufacturing a turbine engine component comprising the steps of: providing a plurality of ceramic plies, each ply comprising woven ceramic fiber tows; providing a plurality of fugitive fibers tows; laying up the plurality of plies in a preselected arrangement to form a turbine engine component shape; inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such that the fugitive fiber tows pass through at least two ceramic plies; burning off the fugitive fiber tows, the burning producing through-thickness void regions; 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, filling the through-thickness void regions with carbon-containing slurry; and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component with in-situ ceramic matrix plugs formed where the through-thickness void regions were located. 2. The method of claim 1, wherein the ceramic fiber tows comprise silicon-carbide containing fibers. 3. The method of claim 1, wherein the plurality of tows are inserted using a method selected from the group consisting of T-forming, Z-pinning, stitching, and combinations thereof. 4. The method of claim 3, wherein the plurality of fugitive tows are inserted using Z-pinning. 5. The method of claim 3, wherein the plurality of fugitive tows are inserted using T-forming. 6. The method of claim 3, wherein the plurality of fugitive fiber tows are inserted using stitching. 7. The method of claim 3, wherein the insertion is performed by hand. 8. The method of claim 3, wherein the insertion is performed by machine. 9. The method of claim 1, wherein the step of burning is performed in an oxygen-containing atmosphere at a temperature in the range of about 50° C. to about 1000° C., for a period of time in the range of about 1 hour to about 100 hours. 10. The method of claim 1, wherein the fugitive fibers are selected from the group consisting of cotton, rayon, nylon, and combinations thereof. 11. The method of claim 1, wherein the plies are silicon carbide containing plies selected from the group consisting of balanced plies, biased plies, and combinations thereof. 12. The method of claim 1, wherein the turbine engine component is a turbine blade. 13. The method of claim 1, wherein the turbine engine component is an uncooled turbine blade. 14. The method of claim 1, wherein the turbine engine component is a cooled turbine blade. 15. The method of claim 1, wherein the turbine engine component is a cooled turbine nozzle. 16. The method of claim 1, wherein the turbine engine component is an uncooled turbine nozzle. 17. The method of claim 1, wherein the step of burning is performed in an oxygen-containing atmosphere at a temperature in the range of about 400° C. to about 800° C., for a period of time in the range of about 2 hours to about 10 hours. 18. A ceramic matrix composite turbine engine component manufactured using the process of claim 1. 19. The ceramic matrix composite turbine engine of claim 1, wherein the component is a cooled turbine shroud. 20. The ceramic matrix composite of claim 1, wherein the component is an uncooled turbine shroud.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (26)
Burchell Timothy D. ; Weaver Charles E. ; Chilcoat Bill R. ; Derbyshire Frank ; Jagtoyen Marit, Activated carbon fiber composite material and method of making.
Steibel James D. ; Corman Gregory S. ; Schikner Robert C. ; Szweda Andrew, Article and method for making complex shaped preform and silicon carbide composite by melt infiltration.
Morrison, Jay; Butner, Steven C.; Campbell, Christian X.; Albrecht, Harry A.; Shteyman, Yevgeuiy, Ceramic matrix composite structure having integral cooling passages and method of manufacture.
Hillig William B. (Ballston Lake NY) McGuigan Henry C. (Schenectady NY), Method of forming fiber- and filament-containing ceramic preform and composite.
Newkirk Marc Stevens (Newark DE) Zwicker Harry Richard (Glen Mills PA) Urquhart Andrew Willard (Newark DE) Biel John Peter (New Castle DE) Kuszyk Jack Andrew (Lincoln University PA) Shumaker Craig Ba, Methods of making composite ceramic articles having embedded filler.
Uskert, Richard C.; Thomas, David J.; Steffier, Wayne S.; Shinavski, Robert J.; Chamberlain, Adam L., Gas turbine engine composite vane assembly and method for making same.
Podgorski, Michael; Dambrine, Bruno Jacques Gerard; Molliex, Ludovic Edmond Camille; Mereaux, Beryl Cassandre Anne, Method for manufacturing an oxide/oxide composite material turbomachine blade provided with internal channels.
Merrill, Gary B.; Morrison, Jay A., Subsurface inclusions of objects for increasing interlaminar shear strength of a ceramic matrix composite structure.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.