Premixing fuel injectors and methods of use in gas turbine combustor
US10690349B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 1, 2017 |
| Grant date | Jun 23, 2020 |
| Priority date | — |
| Expiry date | Jul 24, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00004
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fuel injector for a gas turbine combustor includes side wall fuel injection bodies extending between opposite end walls. Each side wall fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in communication with the fuel plenum. One or more fuel injection bodies extending between the end walls are positioned between the side wall fuel injection bodies. Each fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in fluid communication with the fuel plenum. A conduit fitting coupled to the frame is fluidly connected to the respective fuel plenums. The fuel injection ports fluidly communicate with air flow paths defined between the fuel injection bodies and the side wall fuel injection bodies. A combustor for a gas turbine includes a liner and an axial fuel staging system with the present fuel injector.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.