Methods and systems to thermally protect fuel nozzles in combustion systems
US8607569B2 · kind B2 · utility
9Cited by
12References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 1, 2009 |
| Grant date | Dec 17, 2013 |
| Priority date | — |
| Expiry date | Oct 16, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49229
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of assembling a gas turbine engine is provided. The method includes coupling a combustor in flow communication with a compressor such that the combustor receives at least some of the air discharged by the compressor. A fuel nozzle assembly is coupled to the combustor and includes at least one fuel nozzle that includes a plurality of interior surfaces, wherein a thermal barrier coating is applied across at least one of the plurality of interior surfaces to facilitate shielding the interior surfaces from combustion gases.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.