Axial stage combustor for gas turbine engines
US9068748B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jan 24, 2011 |
| Grant date | Jun 30, 2015 |
| Priority date | — |
| Expiry date | Jul 25, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine includes a radially inboard liner, a radially outboard liner, and a bulkhead that cooperatively define an annular combustion chamber, a plurality of first fuel injectors that are disposed in the bulkhead, and a plurality of second fuel injectors that are disposed in at least one of the inboard liner and the outboard liner aftward of the bulkhead. A method is also provided for operating the combustor of the gas turbine engine wherein fuel distribution between the forward combustion zone and the downstream combustion zone is selectively varied in response to the power operating mode of the gas turbine engine with an objective to control NOx formation.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.