General Electric Company
Gas Turbine Engine Health Determination

Abstract:

A method for determining an engine heath of an aircraft engine includes determining, by one or more control devices, the aircraft engine is operating in a bleed off condition; determining, by the one or more control devices, a first engine health modifier value while the aircraft engine is operating in the bleed off condition, the first of engine health modifier value including a compressor leakage flow value; determining, by the one or more control devices, a second plurality of engine health modifier values while the aircraft engine is operating in a bleed on condition; and determining, by the one or more control devices, an engine health parameter using at least one of the second plurality of engine health modifier values determined while the aircraft engine is operating in the bleed on condition and the compressor leakage flow value determined while the aircraft engine was operating in the bleed off condition.