Gas turbine engine systems and related methods involving thermally isolated retention
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
A47B-097/00
F16M-013/00
D06F-079/02
A47G-023/02
B65D-063/00
B64D-013/00
출원번호
US-0112470
(2008-04-30)
등록번호
US-8235345
(2012-08-07)
발명자
/ 주소
Sadil, Andreas
Barnett, Jr., Claude I.
Daigle, Ricky A.
출원인 / 주소
United Technologies Corp.
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
5인용 특허 :
25
초록▼
Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from bei
Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts.
대표청구항▼
1. An assembly for a gas turbine engine comprising: a mounting surface having a first flange portion and a first mounting orifice, the first flange portion having a first underside, a first aperture and a first free end, the first underside being spaced from and adjacent to the mounting surface such
1. An assembly for a gas turbine engine comprising: a mounting surface having a first flange portion and a first mounting orifice, the first flange portion having a first underside, a first aperture and a first free end, the first underside being spaced from and adjacent to the mounting surface such that a first channel is formed therebetween, the first aperture being aligned with the first mounting orifice;a first component having a first body and a first leg, the first leg extending outwardly from the first body, the first leg having a first recess, the first leg being sized and shaped to be positioned at least partially within the first channel; anda first fastener having a first diameter portion and a second diameter portion, the second diameter portion being narrower than the first diameter portion, the first fastener being fastened to the mounting surface and the first flange with the first diameter portion extending through the first mounting orifice and the first recess, and the second diameter portion extending through the first aperture of the first flange such that the first fastener maintains a spacing between the first underside of the first flange and the mounting surface for permitting movement of the component relative to the mounting surface during thermal cycling of the gas turbine engine. 2. The assembly of claim 1, wherein: the mounting surface has a second flange portion and a second mounting orifice;the second flange portion has a second underside, a second aperture and a second free end, the second underside being spaced from and adjacent to the mounting surface such that a second channel is formed therebetween;the second aperture is aligned with the second mounting orifice; anda first end being spaced from the second end such that a gap is formed therebetween. 3. The assembly of claim 2, wherein: the component has a second leg extending outwardly from the body, the second leg having a second recess and being sized and shaped to be positioned at least partially within the second channel. 4. The assembly of claim 3, further comprising: a second fastener having a first diameter portion and a second diameter portion, the second diameter portion of the second fastener being narrower than the first diameter portion of the second fastener, the second fastener being fastened to the mounting surface and the second flange with the first diameter portion of the second fastener extending through the second mounting orifice and the second recess, and the second diameter portion of the second fastener extending through the second aperture of the second flange such that the second fastener maintains a spacing between the second underside of the second flange and the mounting surface for permitting movement of the component relative to the mounting surface during thermal cycling of the gas turbine engine. 5. The assembly of claim 1, wherein the movement of the first component relative to the mounting surface comprises sliding movement. 6. The assembly of claim 1, wherein the first fastener is a rivet. 7. The assembly of claim 1, wherein the first body of the first component has a first housing and a first bore extending at least partially through the first housing. 8. The assembly of claim 1, wherein the mounting surface is a mounting surface of a flame holder assembly of a gas turbine engine augmentor. 9. The assembly of claim 1, wherein: the first fastener has a head and a tip;the head is located such that the mounting surface is positioned between the head and the first leg. 10. The assembly of claim 9, wherein the tip is located such that the first flange is positioned between the tip and the first leg. 11. The assembly of claim 9, wherein the first diameter portion extends between the head and the second diameter portion. 12. The assembly of claim 1, wherein: the mounting surface has a third flange portion and a third mounting orifice, the third flange portion having a third underside, a third aperture and a third free end, the third underside being spaced from and adjacent to the mounting surface such that a third channel is formed therebetween, the third aperture being aligned with the third mounting orifice;the assembly further comprises a second component having a body and a first leg, the first leg of the second component being sized and shaped to be positioned at least partially within the third channel. 13. The assembly of claim 12, wherein the second component is attached to the mounting surface such that the second component moves relative to the mounting surface. 14. The assembly of claim 12, wherein the second component is attached to the mounting surface such that the second component is fixed relative to the mounting surface.
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이 특허에 인용된 특허 (25)
Taaffe Gary M. (48 Lakeview Crescent Forster AUX 2428), Anchoring device and method.
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Dierberger James A. (Hebron CT) Ackermann William (East Hartford CT) Fine Arthur D. (West Hartford CT), Prestressed combustor liner for gas turbine engine.
Ruberte Sanchez, Jose E.; Wong, Joey; Ricciardo, Mark J.; Hanson, Russell B., Alignment system and methodology to account for variation in a gas turbine engine.
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