Patent ID: 12006881

Abstract:
A method of controlling a combustor of a gas turbine engine is disclosed. The method comprising the steps supplying a total fuel quantity to the combustor dependent on a load of the gas turbine engine, the total fuel quantity is split into a pilot fuel quantity and a main fuel quantity via a pilot fuel split, monitoring at least one signal of at least one condition of the gas turbine engine, generating a steady state value of the at least one signal indicative of a steady state of the gas turbine engine, detecting a change in the at least one signal from the steady-state value. When the change in the at least one signal from the steady state value exceeds a predetermined limit, the method applies the steps generating a transient split offset for the pilot fuel split from a look-up table and applying the transient split offset to the pilot fuel split while maintaining the total fuel quantity being supplied at any point in time.