Fuel injection locations based on combustor flow path
US10718525B2 · kind B2 · utility
2Cited by
6References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 27, 2016 |
| Grant date | Jul 21, 2020 |
| Priority date | — |
| Expiry date | May 13, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/99
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.