Method and system for identifying gas turbine engine faults
First Claim
1. A method for distinguishing between gas turbine engine case cooling (TCC) and high pressure turbine (HPT) performance faults comprising:
- acquiring in-flight gas path data samples corresponding to a predetermined number of engine parameter percent As from nominal;
determining if a percent A shift has occurred in a gas path engine parameter percent A;
if a percent A signature shift has occurred, determining whether the shift AA is from an HPT or TCC performance fault comprising;
extracting exhaust gas temperature shift magnitudes from the predetermined number of engine parameters;
calculating an exhaust gas temperature differential between in-flight and take-off exhaust gas temperature margin calculations, wherein the exhaust gas temperature differential is the difference between the change in exhaust gas temperature margin and the exhaust gas temperature shift magnitudes; and
calculating a TCC event likelihood and a non-TCC event likelihood, wherein if the TCC event is greater than or equal to the non-TCC event likelihood, declaring a TCC fault.
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Abstract
An isolation method and system is described for distinguishing between turbine case cooling (TCC) and high pressure turbine (HPT) performance faults. A trend is observed in gas path parameter data during cruise and a resulting percent Δ signature across the shift in the gas path parameters is assignable to either an HPT or TCC performance fault. During either fault, exhaust gas temperature (EGT) will shift upward. Since take-off EGT margin is calculated from take-off data, the shift, or lack of shift in EGT margin may be used to differentiate between TCC and HPT faults.
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Citations
12 Claims
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1. A method for distinguishing between gas turbine engine case cooling (TCC) and high pressure turbine (HPT) performance faults comprising:
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acquiring in-flight gas path data samples corresponding to a predetermined number of engine parameter percent As from nominal; determining if a percent A shift has occurred in a gas path engine parameter percent A; if a percent A signature shift has occurred, determining whether the shift AA is from an HPT or TCC performance fault comprising; extracting exhaust gas temperature shift magnitudes from the predetermined number of engine parameters; calculating an exhaust gas temperature differential between in-flight and take-off exhaust gas temperature margin calculations, wherein the exhaust gas temperature differential is the difference between the change in exhaust gas temperature margin and the exhaust gas temperature shift magnitudes; and calculating a TCC event likelihood and a non-TCC event likelihood, wherein if the TCC event is greater than or equal to the non-TCC event likelihood, declaring a TCC fault. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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Specification