Gas turbine and gas turbine combustor
US6634175B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 9, 2001 |
| Grant date | Oct 21, 2003 |
| Priority date | — |
| Expiry date | Feb 9, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/04
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor has homogenous air inflow by elimination of turbulence from the air, reducing combustion instability. A combustor 3 has, at its center, a pilot nozzle 8 and eight main nozzles 7 around the pilot nozzle 8. The air flows in around the individual nozzles 7 and 8 to the leading end of the combustor 3 so that it is used for combustion. An annular flow ring 20, having a semicirculat section, is disposed at the upstream end portion of a combustion cylinder 10, and a porous plate 50 and a surrounding rib 51 are disposed downstream of the flow ring 20. The air inflow is smoothly turned at first by the flow ring 20 and then straightened by the porous plate 50 so that the air flows without any disturbance around the individual nozzles 7 and 8 to the leading end, thereby reducing combustion instability.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.