Patent ID: 7752850
Filing Date: 2010-07-13
Classification: F23R

Abstract:
1. A combustor for a gas turbine comprising: a main burner oxidizer flow path delivering a first portion of an oxidizer flow to a main burner of a gas turbine combustor; a pilot oxidizer flow path delivering a second portion of the oxidizer flow to a pilot of the combustor; a flow controller disposed in the pilot oxidizer flow path for controlling an amount of the second portion delivered to the pilot; a pilot fuel flow for delivering fuel to the pilot; and a flow controller actuator controlling a position of the flow controller responsive to an operating condition of the gas turbine; wherein the flow controller comprises a plurality of maintainable open positions between a fully opened state and a fully closed state; and wherein the position of the flow controller is correlated with the amount of fuel to the pilot; and wherein the flow controller actuator is configured to selectively reduce the amount of the second portion delivered to the pilot via maintenance of a position of the flow controller at one of the plurality of maintainable open positions between the fully opened state and the fully closed state as an amount of fuel delivered to the pilot is reduced.