Axially staged gas turbine combustor with interstage premixer
US9851107B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 18, 2014 |
| Grant date | Dec 26, 2017 |
| Priority date | — |
| Expiry date | Aug 24, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/06
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present invention discloses a novel and improved apparatus and method for reducing the emissions of a gas turbine combustion system. More specifically, a combustion system is provided having a first combustion chamber and a premixer positioned proximate an outlet end of a combustion liner for mixing a second fuel/air mixture with hot combustion gases and burning the subsequent mixture to achieve reduced emissions levels. The premixer is positioned generally about the combustion liner and includes a plurality of channels and fuel injectors for introducing a fuel/air mixture, induced with a swirl, into a second, axially staged combustor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.