Gas turbine combustor and gas turbine
US5660045A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jul 14, 1995 |
| Grant date | Aug 26, 1997 |
| Priority date | — |
| Expiry date | Jul 14, 2015 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/00008
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present invention has an object to provide a gas turbine combustor which is able to effect stable combustion in a wide range of fuel flow rate. A burner 1 is provided with fuel nozzles 31 and 32. When a fuel flow rate is small, diffusion flame is formed with fuel supplied from the nozzle 31 with a ring-shaped flame stabilizer 11. Next, fuel is supplied from the nozzle 32 to mix with air, reach to the flame stabilizer 11 and be held by the diffusion flame already formed, whereby stable premixed flames are formed in the flame stabilizer 11 from a range of low fuel air ratio. Further, when flame is propagated from the burner 1 to the burner 2, a fuel air ratio at the outer periphery side of the burner 1 is locally raised by the fuel supplied from the nozzle 31, whereby the combustion stability can be raised in a wide range of fuel flow rate and propagation of flame to adjacent burners becomes easy.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.