Gas turbine engine and combustor having air inlets and pilot burner
US11378277B2 · kind B2 · utility
0Cited by
12References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 23, 2018 |
| Grant date | Jul 5, 2022 |
| Priority date | — |
| Expiry date | Jul 21, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03343
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.