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Using deformation modes to identify cracks in turbine engine compressor disks

Published online by Cambridge University Press:  03 February 2016

R. A. Brockman ,
R. John  and
M. A. Huelsman
R. A. Brockman
Affiliation:
Robert.Brockman@udri.udayton.edu, University of Dayton Research Institute Dayton, Ohio, USA
R. John
Affiliation:
Reji.John@WPAFB.AF.MIL, US Air Force Research Laboratory, Materials and Manufacturing Directorate, AFRL/RXLMN, Wright-Patterson Air Force Base, Ohio, USA
M. A. Huelsman
Affiliation:
University of Dayton Research Institute, Dayton, Ohio, USA
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Abstract

Recent studies show that analytical predictions of crack growth in rotating components can be used in conjunction with displacement measurement techniques to identify critical levels of fatigue damage. However, investigations of this type traditionally have focused on the detection of damage at known flaw locations. This paper addresses the related problem of estimating damage associated with flaws at unknown locations, through the combined use of analytical models and measured vibration signatures. Because the measured data are insufficient to identify a unique solution for the location and severity of fatigue cracks, the function of the analytical model is to bound the extent of damage occurring at life-limiting locations. The prediction of remaining life based on estimates of worst-case fatigue damage and crack locations also is discussed.

Type
Research Article
Information
The Aeronautical Journal , Volume 113 , Issue 1150: Flight structures fundamental research in the United States of America: A Special Issue – PART II , December 2009 , pp. 811 - 819
Copyright
Copyright © Royal Aeronautical Society 2009 

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