Combustion chamber for a gas turbine engine
US7857094B2 · kind B2 · utility
21Cited by
10References
7Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 31, 2007 |
| Grant date | Dec 28, 2010 |
| Priority date | — |
| Expiry date | Oct 13, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00014
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion chamber for a gas turbine engine comprising at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the interior of the combustion chamber. The cavity extends around at least part of the neck and is spaced apart therefrom to define a cooling chamber therebetween. The cooling chamber allows the neck and the cavity to be cooled with a flow of cooling air. The sunken neck allows the resonator to be located within enclosures with minimal volume without compromising on the damping properties afforded.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.