Lean-rich axial stage combustion in a can-annular gas turbine engine
US9366443B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 11, 2013 |
| Grant date | Jun 14, 2016 |
| Priority date | — |
| Expiry date | Oct 25, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/286
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.