Gas turbine combustor sliding joint
US7000406B2 · kind B2 · utility
16Cited by
17References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 3, 2003 |
| Grant date | Feb 21, 2006 |
| Priority date | — |
| Expiry date | Feb 8, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor. The vane assembly includes at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween. At least the outer platform forms a first sliding joint connection with an adjacent outer combustor wall such that radial sealing between the outer platform and the outer combustor wall is provided at engine operating temperature, while permitting relative axial displacement therebetween.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.