ACOUSTIC DIAGNOSTIC OF FIELDED TURBINE ENGINES
First Claim
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1. A method for diagnosing faults in an aircraft gas turbine engine, the method comprising:
- gathering an acoustic profile from an on-wing turbine;
transmitting the acoustic profile to an analysis system;
comparing the acoustic profile with known fault profiles in a library of the analysis system; and
scheduling maintenance steps based on whether the acoustic profile matches one or more of the known fault profiles.
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Abstract
A method for diagnosing faults in an aircraft gas turbine engine comprises gathering an acoustic profile from an on-wing turbine, transmitting the acoustic profile to an analysis system, comparing the acoustic profile with known fault profiles, and scheduling maintenance steps based on whether the acoustic profile matches one or more of the known fault profiles. The known fault profiles are retrieved from a library of the analysis system.
48 Citations
20 Claims
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1. A method for diagnosing faults in an aircraft gas turbine engine, the method comprising:
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gathering an acoustic profile from an on-wing turbine; transmitting the acoustic profile to an analysis system; comparing the acoustic profile with known fault profiles in a library of the analysis system; and scheduling maintenance steps based on whether the acoustic profile matches one or more of the known fault profiles. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A system for diagnosing faults in an aircraft gas turbine engine, the system comprising:
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an array of acoustic sensors positioned about an on-wing gas turbine engine; a data acquisition and transmission unit which collects and transmits sensor signals from the acoustic sensors; a signal analysis station which receives and processes the sensor signals, the signal analysis station comprising; a database mapping a plurality of known acoustic signatures to known failure states; and a processor which compares sensor signals to the known acoustic signatures to produce a diagnosis signal. - View Dependent Claims (9, 10, 11, 12, 13, 14, 15)
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16. A method for diagnosing faults in an aircraft gas turbine engine, the method comprising:
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gathering acoustic data from a plurality of acoustic sensors situated about an on-wing turbine; extracting a plurality of features from the acoustic data to form an acoustic profile; comparing the acoustic profile to a plurality of library profiles from a signature library, the library profiles corresponding to known failure or non-failure modes of the gas turbine engine; and scheduling appropriate maintenance for failure modes corresponding to library profiles matching the acoustic profile. - View Dependent Claims (17, 18, 19, 20)
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Specification