Combustor assembly for a turbine engine
US11022313B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 22, 2016 |
| Grant date | Jun 1, 2021 |
| Priority date | — |
| Expiry date | Dec 30, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.