Systems and methods for cooling gas turbine engine transition liners
US7954326B2 · kind B2 · utility
7Cited by
19References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 28, 2007 |
| Grant date | Jun 7, 2011 |
| Priority date | — |
| Expiry date | Feb 5, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine assembly includes a combustor configured to combust an air-fuel mixture to produce combustion gases in a first direction; a transition liner coupled to the combustor and adapted to receive the combustion gases from the combustor and to redirect the combustion gases in a second direction; and a turbine coupled to the transition liner and adapted to receive the combustion gases from the transition liner. The transition liner has a plurality of effusion holes that include a first group that extend at least partially in a tangential direction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.