Operation of a combustor apparatus in a gas turbine engine
US8726671B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 14, 2010 |
| Grant date | May 20, 2014 |
| Priority date | — |
| Expiry date | Mar 19, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/00
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.