Fuel injection assemblies for axial fuel staging in gas turbine combustors
US11187415B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 11, 2017 |
| Grant date | Nov 30, 2021 |
| Priority date | — |
| Expiry date | Jul 27, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.