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Hybrid Kalman Filter Approach for Aircraft Engine In-Flight Diagnostics: Sensor Fault Detection Case

[+] Author Affiliations
Takahisa Kobayashi

QSS Group, Inc., Cleveland, OH

Donald L. Simon

NASA Glenn Research Center, Cleveland, OH

Paper No. GT2006-90870, pp. 745-755; 11 pages
doi:10.1115/GT2006-90870
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 2: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Controls, Diagnostics and Instrumentation; Environmental and Regulatory Affairs
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4237-1 | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

In this paper, a diagnostic system based on a uniquely structured Kalman filter is developed for its application to inflight fault detection of aircraft engine sensors. The Kalman filter is a hybrid of a nonlinear on-board engine model (OBEM) and piecewise linear models. The utilization of the nonlinear OBEM allows the reference health baseline of the diagnostic system to be updated, through a relatively simple process, to the health condition of degraded engines. Through this health baseline update, the diagnostic effectiveness of the in-flight sensor fault detection system is maintained as the health of the engine degrades over time. The performance of the sensor fault detection system is evaluated in a simulation environment at several operating conditions during the cruise phase of flight.

Copyright © 2006 by ASME

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