Patent ID: 7640725
Filing Date: 2010-01-05
Classification: F02C,F05D,F23N,F23R

Abstract:
1. A method for controlling combustion in a gas turbine pilot combustor, comprising: adjusting a premix fuel flow amount of a pilot fuel flow provided to a premix burner stage of a pilot of a gas turbine combustor from a preset premix fuel flow amount to an adjusted premix fuel flow amount to achieve a first operating condition of the combustor that is closer to a dynamically unstable condition than before the premix fuel flow amount was adjusted, in order to reduce pollutant formation; and adjusting subsequently a diffusion fuel flow amount of the pilot fuel flow provided to a diffusion burner stage of the pilot from a preset diffusion fuel flow amount to an adjusted diffusion fuel flow amount to achieve a second operating condition of the combustor that closer to a dynamically unstable condition than before the diffusion fuel flow amount was adjusted, in order to further reduce pollutant formation.