Premix combustor for gas turbine engine
US6189314A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 30, 1999 |
| Grant date | Feb 20, 2001 |
| Priority date | — |
| Expiry date | Aug 30, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23D2900/11101
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A premixing section for supplying a fuel-air mixture to a homogeneous combustion chamber includes a first fuel nozzle disposed along an axis, a second fuel nozzle disposed to surround the outer periphery of the first fuel nozzle, and a premixing/pre-evaporating chamber. The first fuel nozzle is a diffusion combustion type nozzle and supplies the fuel-air mixture from an air blast-type nozzle tip directly to the homogeneous combustion chamber. The second fuel nozzle is a premixing/pre-evaporating type nozzle and supplies the fuel-air mixture from an air blast-type nozzle tip to the premixing/pre-evaporating chamber, so that the fuel-air mixture promoted in mixing and evaporation in the premixing/pre-evaporating chamber, is supplied via a swirler to the homogeneous combustion chamber. With the above arrangement, the atomization of the fuel enhances the emission characteristics.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.