System and method of improving combustion stability in a gas turbine
US11592178B2 · kind B2 · utility
1Cited by
5References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 15, 2019 |
| Grant date | Feb 28, 2023 |
| Priority date | — |
| Expiry date | Jul 17, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02E20/34
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine having a compressor upstream of the combustor and a turbine downstream of the combustor. The combustor also includes a combustor chamber, an oxy-fuel pilot burner (104) centrally positioned at an end of the combustor chamber, and an air-fuel premix burner configured to at least partially premix air and fuel. The air-fuel premix burner surrounds the oxy-fuel pilot burner (104) in an annular configuration.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.