Pressure dynamics reduction within a gas turbine engine

摘要

A method for pressure dynamics reduction within a gas turbine engine with a number of combustion chambers (1), where a pilot fuel spilt is defined for each combustion chamber, is provided, comprising the steps of measuring the pressure values in each combustion chamber in time steps (21), determining the pressure change rates in the combustion chambers from the measured pressure values, and reducing the pilot fuel split to a particular combustion chamber to zero (26) in case that the pressure change rate in this combustion chamber increases over two or more consecutive time steps (23) and exceeds the pressure change rate in all other combustion chambers (25) and the pressure change rate in this combustion chamber is above a maximum allowable pressure change limit (24).