Combustor for a gas turbine engine
US11371701B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 3, 2021 |
| Grant date | Jun 28, 2022 |
| Priority date | — |
| Expiry date | Feb 3, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03042
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine includes a forward liner segment and an aft liner segment positioned downstream from the forward liner segment relative to a direction of flow through the combustor. The forward and aft liner segments at least partially define a combustion chamber. Furthermore, the combustor includes a dilution slot frame positioned between the forward and aft liner segments along a longitudinal centerline of the gas turbine engine. Moreover, the dilution slot frame defines a plurality of dilution slots spaced apart from each other along a circumferential direction of the gas turbine engine such that the plurality of dilution slots provides an annular ring of dilution air to the combustion chamber.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.