CONTROL METHOD FOR PILOT AND PREMIX FUEL FLOW SPLIT FOR A GAS TURBINE COMBUSTOR

摘要

A control system (110) and method for controlling the split between premix fuel flow and pilot fuel flow to a combustor (10) in a gas turbine engine (1) are presented, so that acceptable emission levels are maintained. Engine speed and exhaust gas temperature are used in the equation Tpz = ( theta EGT)1 x (N/ theta <0.5> DIVIDED K2) to obtain a combustor pilot zone temperature that will result in the desired level of emissions. From this pilot zone temperature a desired split between premix fuel flow and pilot fuel flow is obtained and compared to the actual split to generate an error signal. The actual premix fuel flow and pilot fuel flow are then adjusted until the desired split and hence the desired emission levels are obtained.