Combustor resonator section with an internal thermal barrier coating and method of fabricating the same
US9395082B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 19, 2012 |
| Grant date | Jul 19, 2016 |
| Priority date | — |
| Expiry date | May 7, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor (100) for a gas turbine engine (30) has a circumferentially extending liner (109) defining at least a portion of an interior combustion chamber (107) and a hot gas path (115). The liner includes a resonator section (112) including at least one resonator (116A, 116B) having a resonator chamber (125A, 125B) formed on an exterior of the liner. A thermal barrier coating (118) is disposed along an inner surface of the liner including an inner surface (130) of the resonator section. The resonator further includes a plurality of apertures (117) and each aperture extends through the liner and the thermal barrier coating at the resonator section and there is fluid flow communication between the combustion chamber and the resonator chamber.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.