Seal for gas turbine nozzle and shroud interface
US6659472B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 28, 2001 |
| Grant date | Dec 9, 2003 |
| Priority date | — |
| Expiry date | Dec 28, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16J15/0887
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a gas turbine including a nozzle retaining ring having a first annular axially sealing surface and a shroud segment having an axial registering second surface. To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal having reversely folded U-shaped marginal portions is received in a cavity formed in the second surface. At operating conditions, the marginal portions seal against the base of the cavity and the first surface of the retaining ring to prevent leakage flow past the retaining ring/shroud segment interface. To install the seal, the seal body is first compressed and maintained in a compressed state by applying one or more wraps about the seal body and an epoxy is used to secure the seal when compressed in the cavity. At operating temperatures, the retention means releases the seal to engage marginal portions against opposite sealing surfaces of the shroud segments and retaining ring.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.