Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10508811B2 · kind B2 · utility
1Cited by
23References
23Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Oct 3, 2016 |
| Grant date | Dec 17, 2019 |
| Priority date | — |
| Expiry date | Oct 24, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased circumferential fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased circumferential fuel distribution within a swirler of a radial fuel injection system.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.