[특허]Method and system for a ceramic matrix composite shroud hanger assembly

Method and system for a ceramic matrix composite shroud hanger assembly 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-011/08 F01D-025/24
출원번호	US-0634060 (2015-02-27)
등록번호	US-9874104 (2018-01-23)
발명자 / 주소	Shapiro, Jason David
출원인 / 주소	General Electric Company
대리인 / 주소	General Electric Company
인용정보	피인용 횟수 : 0 인용 특허 : 65

초록 ▼

A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud.

대표청구항 ▼

1. A shroud and shroud hanger assembly for a gas turbine engine, said assembly comprising: a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion, said shroud hanger assembly includes a diagonal web member that extends from a radially inner end of a forward radially extending leg to a radially outer end of an aftward radially extending leg of said aftward hanger portion; anda shroud formed of a second material having a second coefficient of thermal expansion, said forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of said shroud. 2. The shroud and hanger assembly of claim 1, wherein said forward and aftward hanger portions are configured to couple together using a mechanical fastener connection. 3. The shroud and hanger assembly of claim 1, wherein said forward and aftward hanger portions are configured to couple together using a bolted connection. 4. The shroud and hanger assembly of claim 1, wherein the first coefficient of thermal expansion is equal to the second coefficient of thermal expansion. 5. The shroud and hanger assembly of claim 1, wherein the first and second materials are ceramic matrix composite materials. 6. The shroud and hanger assembly of claim 1, wherein said shroud is supported radially by a pin extending thorough radially outwardly extending walls of said shroud and extending through radially inwardly extending legs of said aftward hanger portion. 7. The shroud and hanger assembly of claim 1, wherein said shroud hanger assembly includes an axial web member extending axially between a forward radially extending leg and an aftward radially extending leg of said aftward hanger portion. 8. The shroud and hanger assembly of claim 1, wherein said aftward hanger portion is supported radially by a first tab extending axially from a radially outer end of a forward leg of said aftward hanger portion and a second tab extending axially from a radially outer end of an aftward leg of said aftward hanger portion, said first and said second tabs configured to engage circumferential lips of a casing surrounding said shroud and hanger assembly. 9. A method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly, said method comprising: clamping a forward hanger portion and a separate aftward hanger portion of a shroud hanger assembly together, a forward radially extending wall of the shroud positioned between the forward hanger portion and the aftward hanger portion, the forward radially extending wall receiving a clamping force on a forward side from the forward hanger portion and on an aftward side from the aftward hanger portion providing a load transfer joint between the shroud and the shroud hanger assembly;coupling the shroud hanger assembly to a casing of a turbine; andtransferring load from a nozzle through a diagonal web member of the shroud hanger assembly to the casing. 10. The method of claim 9, wherein clamping a forward hanger portion and a separate aftward hanger portion comprises clamping the forward radially extending wall between the forward hanger portion and the aftward hanger portion at the load transfer joint. 11. A gas turbine engine comprising: a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion, said shroud hanger assembly includes a diagonal web member that extends from a radially inner end of a forward radially extending leg to a radially outer end of an aftward radially extending leg of said aftward hanger portion; anda shroud formed of a second material having a second coefficient of thermal expansion, said forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of said shroud. 12. The gas turbine engine of claim 11, wherein said forward and aftward hanger portions are configured to couple together using a mechanical fastener connection. 13. The gas turbine engine of claim 11, wherein said forward and aftward hanger portions are configured to couple together using a bolted connection. 14. The gas turbine engine of claim 11, wherein the first coefficient of thermal expansion is equal to the second coefficient of thermal expansion. 15. The gas turbine engine of claim 11, wherein the first and second materials are ceramic matrix composite materials. 16. The gas turbine engine of claim 11, wherein said shroud is supported radially by a pin extending thorough radially outwardly extending walls of said shroud and extending through radially inwardly extending legs of said aftward hanger portion. 17. The gas turbine engine of claim 11, wherein said shroud hanger assembly includes an axial web member extending axially between a forward radially extending leg and an aftward radially extending leg of said aftward hanger portion. 18. The gas turbine engine of claim 11, wherein said aftward hanger portion is supported radially by a first tab extending axially from a radially outer end of a forward leg of said aftward hanger portion and a second tab extending axially from a radially outer end of an aftward leg of said aftward hanger portion, said first and said second tabs configured to engage circumferential lips of a casing surrounding said shroud and hanger assembly.

이 특허에 인용된 특허 (65)

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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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연합인증

Method and system for a ceramic matrix composite shroud hanger assembly 원문보기

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Method and system for a ceramic matrix composite shroud hanger assembly 원문보기

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