Pilot fuel flow tuning for gas turbine combustors
US7640725B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 12, 2006 |
| Grant date | Jan 5, 2010 |
| Priority date | — |
| Expiry date | Aug 4, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23N2241/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method and system for controlling combustion in a gas turbine combustor (18) includes adjusting an amount of a premix fuel portion (30) of a pilot fuel (28) provided to a premix burner stage (48) of a pilot (46) of the gas turbine combustor. The amount of the premix fuel portion is adjusted from a preset premix fuel portion amount to an adjusted premix fuel portion amount to achieve a desired first operating condition of the combustor. An amount of a diffusion fuel portion (34) of the pilot fuel provided to a diffusion burner stage (50) of the pilot is then adjusted from a preset diffusion fuel portion amount to an adjusted diffusion fuel portion amount to achieve a desired second operating condition of the combustor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.