Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine
US10738704B2 · kind B2 · utility
0Cited by
23References
8Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Oct 3, 2016 |
| Grant date | Aug 11, 2020 |
| Priority date | — |
| Expiry date | Feb 24, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply a first percentage of fuel and a radial fuel injection system that communicates with the combustion chamber downstream of the axial fuel injection system, the radial fuel injection system operable to supply a second percentage of fuel, the first percentage and the second percentage of fuel scheduled in response to an engine operating parameter.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.