Fuel flow tuning for a stage of a gas turbine engine
US7805922B2 · kind B2 · utility
24Cited by
10References
17Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Feb 9, 2006 |
| Grant date | Oct 5, 2010 |
| Priority date | — |
| Expiry date | Dec 18, 2028 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C9/26
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method and system for controlling combustion in a gas turbine engine (10) includes reducing an overall fuel flow provided to a stage (22) of burners (e.g. 34, 35) of the gas turbine engine until reaching a predetermined dynamic operating condition of the first burner of the stage. The method also includes maintaining, while continuing to reduce the overall fuel flow (e.g. 30), a first portion (e.g. 36), of the overall fuel flow delivered to the first burner at a maintenance level so that the predetermined dynamic operating condition of the first burner is maintained.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.