Abstract: System and methods for detecting anomalies and identifying faults of a gas turbine engine may include a recorder in communication with a processor. The recorder may be configured to capture archival data of the gas turbine engine. A flight normalizer module may be configured to produce normalized results based on the archival data. A flight parameter features module may be configured to generate flight parameter features based on the normalized results. A data warehouse module may be configured to determine suspected fault classes by comparing the flight parameter features against training parameter features stored in the data warehouse module based on queries from the flight parameter features module. A majority vote module may be configured to determine a diagnosed fault class based on the suspected fault classes.

Abstract: System and methods for detecting anomalies and identifying faults of a gas turbine engine may include a recorder in communication with a processor. The recorder may be configured to capture archival data of the gas turbine engine. A flight normalizer module may be configured to produce normalized results based on the archival data. A flight parameter features module may be configured to generate flight parameter features based on the normalized results. A data warehouse module may be configured to determine suspected fault classes by comparing the flight parameter features against training parameter features stored in the data warehouse module based on queries from the flight parameter features module. A majority vote module may be configured to determine a diagnosed fault class based on the suspected fault classes.

Abstract: An identification system for machinery or equipment, such as an aircraft engine, includes a name plate, a mounting bracket for mounting the name plate, a housing, and an RFID tag positioned within the housing between the name plate and the mounting bracket. The RFID tag includes an integrated circuit and an antenna such as a patch antenna.

Abstract: An RFID tag system includes a housing that includes an enclosed sidewall and forms a recess with a housing base surface, where the housing is configured and arranged to be mounted to a mounting surface. An RFID tag is located within the housing, and the RFID tag comprises an integrated circuit, an antenna and a metal backplane, where the housing base surface separates the antenna and the metal backplane. A metal surface is secured to a top surface of the sidewall to cover the recess, where the metal surface and a transmission path from the integrated circuit to the antenna are electromagnetically coupled and tuned to operate across a wide band frequency range. The metal surface may include a name plate of a data plate for a gas turbine engine, or a component thereof.

Abstract: A fault detection and diagnosis method for a gas turbine engines comprises collecting a sensor signal from an acoustic or vibrational sensor at the gas turbine engine, pre-processing the sensor signal to remove predictable background, and extracting a feature set from the sensor signal using Mel-Frequency Cepstral Coefficients (MFCC) algorithms and/or Code Excited Linear Prediction (CELP) algorithms. Fault and non-fault states are reported based on comparison between the feature set and a library of fault and non-fault feature profiles corresponding to fault and non-fault states of the gas turbine engine.

Abstract: An engine frame comprises an engine support structure and a communication device with a serial number and a wireless transceiver. The engine support structure is configured to support an engine for maintenance or transport. The communication device is configured to determine a location of the engine frame, and broadcast a report message including the location of the engine frame and the serial number to a remote server via the wireless transceiver.

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.

Abstract: A fault detection and diagnosis method for a gas turbine engines comprises collecting a sensor signal from an acoustic or vibrational sensor at the gas turbine engine, pre-processing the sensor signal to remove predictable background, and extracting a feature set from the sensor signal using Mel-Frequency Cepstral Coefficients (MFCC) algorithms and/or Code Excited Linear Prediction (CELP) algorithms. Fault and non-fault states are reported based on comparison between the feature set and a library of fault and non-fault feature profiles corresponding to fault and non-fault states of the gas turbine engine.

Abstract: An RFID tag system includes a housing that includes an enclosed sidewall and forms a recess with a housing base surface, where the housing is configured and arranged to be mounted to a mounting surface. An RFID tag is located within the housing, and the RFID tag comprises an integrated circuit, an antenna and a metal backplane, where the housing base surface separates the antenna and the metal backplane. A metal surface is secured to a top surface of the sidewall to cover the recess, where the metal surface and a transmission path from the integrated circuit to the antenna are electromagnetically coupled and tuned to operate across a wide band frequency range. The metal surface may include a name plate of a data plate for a gas turbine engine, or a component thereof.

Abstract: A method of aircraft maintenance involves storing part information relating to an aircraft part on the aircraft part. The part information is wirelessly transmitting from the aircraft part to a receiver. A note of a change relating to the aircraft part is made. The part information with the note of the change relating to the aircraft part is electronically stored at a location remote from the aircraft part.