Gas turbine engine combustor with improved cooling
US7451600B2 · kind B2 · utility
38Cited by
19References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 6, 2005 |
| Grant date | Nov 18, 2008 |
| Priority date | — |
| Expiry date | Nov 20, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/10
- 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 improved cooling efficiency in regions of the combustor dome corresponding to predetermined hotspots.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.