Sequential combustor gas turbine including a plurality of gaseous fuel injection nozzles and method for operating the same
US9062886B2 · kind B2 · utility
4Cited by
16References
14Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 6, 2011 |
| Grant date | Jun 23, 2015 |
| Priority date | — |
| Expiry date | Feb 24, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03341
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine (1) includes a compressor (2) that feeds an oxidizer to one or more combustion devices (3, 5) in which fuel is injected and is combusted to generate hot gases that are expanded in a turbine (4, 6). The flue gases discharged from the turbine (4, 6) are partially recirculated into the compressor (2). The fuel is a gaseous fuel that is injected into the combustion devices (3, 5) via two or more stages (20, 22, 23). One of the stages is a pilot stage (20) in which the fuel is injected along a longitudinal axis (21) of the combustion device (3, 5) or an axis parallel thereto.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.