Multihole patch for combustor liner of a gas turbine engine
US7086232B2 · kind B2 · utility
15Cited by
20References
22Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 29, 2002 |
| Grant date | Aug 8, 2006 |
| Priority date | — |
| Expiry date | Jun 4, 2023 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from impingement of hot gases, a plurality of cooling slots formed in the shell through which air flows for providing a cooling film along a hot side of the shell, and a group of cooling holes formed in the shell in the discrete region to augment the cooling film and provide convective bore cooling to the discrete region.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.