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An Integrated Architecture for Aircraft Engine Performance Monitoring and Fault Diagnostics: Engine Test ResultsThis paper presents a model-based architecture for performance trend monitoring and gas path fault diagnostics designed for analyzing streaming transient aircraft engine measurement data. The technique analyzes residuals between sensed engine outputs and model predicted outputs for fault detection and isolation purposes. Diagnostic results from the application of the approach to test data acquired from an aircraft turbofan engine are presented. The approach is found to avoid false alarms when presented nominal fault-free data. Additionally, the approach is found to successfully detect and isolate gas path seeded-faults under steady-state operating scenarios although some fault misclassifications are noted during engine transients. Recommendations for follow-on maturation and evaluation of the technique are also presented.
Document ID
20150000899
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Rinehart, Aidan W. (Vantage Partners, LLC Brook Park, OH, United States)
Simon, Donald L. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
January 30, 2015
Publication Date
January 1, 2015
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 2014-3924
GRC-E-DAA-TN17165
E-19012
NASA/TM-2015-218448
Meeting Information
Meeting: Joint Propulsion Conference
Location: Cleveland, OH
Country: United States
Start Date: July 28, 2014
End Date: July 30, 2014
Sponsors: Society of Automotive Engineers, Inc., American Inst. of Aeronautics and Astronautics, American Society for Electrical Engineers
Funding Number(s)
CONTRACT_GRANT: NNC12BA01B
WBS: WBS 284848.02.04.03.02.01.03
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
systems health monitoring
gas turbine engines
propulsion system performance

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