[특허]Seals for a circumferential stop ring in a turbine exhaust case

Seals for a circumferential stop ring in a turbine exhaust case 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-011/00 F01D-025/16 F01D-025/24
출원번호	US-0730899 (2012-12-29)
등록번호	US-9771818 (2017-09-26)
발명자 / 주소	Budnick, Matthew Chuong, Conway Scott, Jonathan A.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Kinney & Lange, P.A.
인용정보	피인용 횟수 : 0 인용 특허 : 103

초록 ▼

A turbine seal system comprises an annular structural frame, a circumferential ring, a fairing and a seal. The circumferential ring is joined to the annular structural frame. The fairing is disposed within the annular structural frame and is engaged with the circumferential ring to limit circumferential rotation of the fairing with respect to the annular structural frame. The seal extends between the fairing and the circumferential ring. In one embodiment, the structural component comprises a ring-strut-ring turbine exhaust case.

대표청구항 ▼

1. A turbine seal system comprising: an annular structural frame;a circumferential ring joined to the annular structural frame, the circumferential ring comprising: an annular ring body engaged with the annular structural frame;a circumferential stop comprising slots projecting radially inward from the annular ring body; anda seal land projecting axially from the annular ring body;a fairing disposed within the annular structural frame and engaged with the circumferential stop to limit circumferential rotation of the fairing with respect to the annular structural frame, wherein the fairing includes lugs extending axially so as to be interposed with the slots; anda seal extending between the fairing and the circumferential ring to engage the seal land. 2. The turbine seal system of claim 1 and further comprising: a backing plate extending radially from the annular ring body; anda plurality of bolt holes extending through the backing plate. 3. The turbine seal system of claim 1 wherein the seal land projects axially aftward from an inner diameter of the annular ring body. 4. The turbine seal system of claim 1 wherein the seal land projects axially aftward from an outer diameter of the annular ring body. 5. The turbine seal system of claim 1 wherein the seal comprises: a first end coupled to the fairing; anda second end biased against the seal land. 6. The turbine seal system of claim 5 and further comprising: a second seal comprising: a first end coupled to the annular ring body; anda second end extending aftward so as to be configured to engage a structural component joined to the annular structural frame. 7. The turbine seal system of claim 1 wherein the seal comprises: a first end coupled to the fairing; anda second end secured between the seal land and the annular structural frame. 8. The turbine seal system of claim 7 and further comprising: a coupling flange extending from the fairing; andan attachment ring joined to the coupling flange;wherein the first end of the seal is secured between the coupling flange and the attachment ring. 9. The turbine seal system of claim 1 and further comprising means for inhibiting circumferential rotation of the fairing within the frame. 10. A circumferential stop ring for a gas turbine engine structural member and fairing, the circumferential stop ring comprising: an annular ring body for joining to the structural member;a plurality of circumferential stop lugs projecting radially inward from the annular ring body for engaging the fairing; anda seal land projecting axially aftward from the annular ring body to provide a seal surface; anda plurality of bolt holes extending through the annular ring body, wherein the seal land is positioned radially outward of the plurality of bolt holes. 11. A gas turbine engine structural system comprising: a frame comprising: an outer ring;an inner ring; anda plurality of struts joining the outer ring and the inner ring;a fairing coupled to the plurality of struts between the outer ring and the inner ring;a circumferential stop ring joined to the outer ring at a bolted connection and engaged with the fairing, the circumferential stop ring including a seal land that projects axially aftward from the circumferential stop ring radially outward of the bolted connection; anda seal extending between the fairing and the seal land. 12. The turbine seal system of claim 11 wherein the seal comprises: a first end coupled to the fairing; anda second end secured between the seal land and the outer ring. 13. A turbine seal system comprising: an annular structural frame;a circumferential ring joined to the annular structural frame, the circumferential ring comprising: an annular ring body engaged with the annular structural frame;a circumferential stop projecting radially from the annular ring body; anda seal land projecting axially from the annular ring body;a fairing disposed within the annular structural frame and engaged with the circumferential stop to limit circumferential rotation of the fairing with respect to the annular structural frame; anda first seal extending between the fairing and the circumferential ring to engage the seal land, the first seal comprising: a first end coupled to the fairing; anda second end biased against the seal land; anda second seal comprising: a first end coupled to the annular ring body; anda second end extending aftward so as to be configured to engage a structural component joined to the annular structural frame. 14. The turbine seal system of claim 13, wherein the circumferential stop ring is joined to the outer ring at a bolted connection. 15. The gas turbine engine structural system of claim 14 wherein the seal land projects axially aftward from the circumferential stop ring radially inward of the bolted connection.

이 특허에 인용된 특허 (103)

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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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Seals for a circumferential stop ring in a turbine exhaust case 원문보기

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Seals for a circumferential stop ring in a turbine exhaust case 원문보기

초록 ▼

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연구과제 타임라인

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