Gas turbine engine combustor with improved cooling
US7624577B2 · kind B2 · utility
7Cited by
33References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 31, 2006 |
| Grant date | Dec 1, 2009 |
| Priority date | — |
| Expiry date | Nov 26, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03042
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in regions intermediate each diffuser pipe than in other areas of the combustor liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.