Patent ID: 7702447
Filing Date: 2010-04-20
Classification: F02C,F05D,G05B

Abstract:
1. A method for distinguishing between gas turbine engine case cooling (TCC) and high pressure turbine (HPT) performance faults comprising: monitoring a plurality of gas path parameters of an operating gas turbine engine so as to acquire in-flight gas path data samples from said gas turbine engine, said in-flight gas path data samples corresponding to a predetermined number of engine parameter percent Δs from nominal; inputting said in-flight gas path data samples into a computer; determining if a percent Δ shift has occurred in a gas path engine parameter percent Δ; if a percent Δ signature shift has occurred, determining whether a shift ΔΔ is from an HPT or TCC performance fault, said shift ΔΔ determining step comprising: obtaining a mean and standard deviation for gas turbine engines not experiencing TCC faults; obtaining a mean and standard deviation for gas turbine engines experiencing TCC faults, and calculating an exhaust gas temperature difference between cruise and take-off conditions.