Gas turbine engine reverse-flow combustor
US8001793B2 · kind B2 · utility
7Cited by
14References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 29, 2008 |
| Grant date | Aug 23, 2011 |
| Priority date | — |
| Expiry date | Jun 20, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple rows of effusion cooling holes, bounded by cooled effusionless bands to aid in repairability of the combustor. The cooling of the bands improves the durability of the combustor and provides a method of repair for the combustor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.