Rope seal for gas turbine engines
First Claim
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1. A seal assembly in a region of a gas turbine engine subject to high operating temperatures, comprising:
- first and second engine components defining first and second mutually confronting surfaces that define a gap therebetween, the gap being variable during operation of the gas turbine engine,a recess in the second surface, the recess having a rear surface that faces toward the first surface,a rope seal element comprising a high-temperature resistant material of at least one of ceramic and metal, anda resilient seal carrier extending lengthways of the rope seal element and in which the rope seal element is located, the rope seal element being trapped between the seal carrier and the first surface to seal against the first surface, the seal carrier being resilient at the operating temperatures of the gas turbine engine to urge the rope seal element against the first surface,the seal carrier having splayed leg portions that seal against the rear surface of the recess, the recess being substantially wider than the splay of the splayed leg portions upon assembly of the first and second components into the engine, and the splayed leg portions being operative to splay further apart on the rear surface of the recess as the gap between the first and second mutually confronting surfaces decreases.
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Accused Products
Abstract
A sealing arrangement in a gas turbine engine comprises a rope seal held against a sealing surface by a resilient seal carrier in which the rope seal lies.
51 Citations
5 Claims
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1. A seal assembly in a region of a gas turbine engine subject to high operating temperatures, comprising:
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first and second engine components defining first and second mutually confronting surfaces that define a gap therebetween, the gap being variable during operation of the gas turbine engine, a recess in the second surface, the recess having a rear surface that faces toward the first surface, a rope seal element comprising a high-temperature resistant material of at least one of ceramic and metal, and a resilient seal carrier extending lengthways of the rope seal element and in which the rope seal element is located, the rope seal element being trapped between the seal carrier and the first surface to seal against the first surface, the seal carrier being resilient at the operating temperatures of the gas turbine engine to urge the rope seal element against the first surface, the seal carrier having splayed leg portions that seal against the rear surface of the recess, the recess being substantially wider than the splay of the splayed leg portions upon assembly of the first and second components into the engine, and the splayed leg portions being operative to splay further apart on the rear surface of the recess as the gap between the first and second mutually confronting surfaces decreases. - View Dependent Claims (2, 3, 4, 5)
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Specification
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Current AssigneeAnsaldo Energia Switzerland AG
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Original AssigneeAlstom Technology Ltd. (Alstom SA)
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InventorsJames, Terence John
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Primary Examiner(s)PATEL, VISHAL A
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Application NumberUS11/205,737Publication NumberTime in Patent Office951 DaysField of Search277608-609, 277/616, 277/637, 277/650, 277/644, 415/135, 415/173.3, 415/174.2, 415174- 3, 415/214.1, 415/231US Class Current277/644CPC Class CodesF01D 11/005 Sealing means between non r...F05C 2201/0466 NickelF05D 2240/55 SealsF05D 2250/70 ShapeF16J 15/0812 with a braided or knitted bodyF16J 15/0887 the sealing effect being ob...F16J 15/22 shaped as strands, ropes, t...F16J 15/3212 with metal springs
