Patent ID: 6408611
Filing Date: 2002-06-25
Classification: F02C,F05D

Abstract:
A method for controlling the split between premix fuel flow and pilot fuel flow to a combustor in a gas turbine engine comprising the steps of:a) sensing an operating condition of said engine and generating a first signal thereof; b) generating a second signal indicative of a desired pilot zone temperature (Tpz) in said combustor from said first signal; c) generating a third signal indicative of a desired split between said premix fuel flow and said pilot fuel flow from said second signal; d) sensing at least one parameter from which one of either the actual premix fuel flow or actual pilot fuel flow can be determined, and generating a fourth signal indicative of said one of actual premix fuel flow or said actual pilot fuel flow; e) comparing said fourth signal to said third signal and generating an error signal therefrom; and f) adjusting the actual premix fuel flow and the actual pilot fuel flow to said combustor until said desired split is substantially reached.