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Practical Aspects of Fatigue Crack Growth in Aero-GTE Applications

[+] Author Affiliations
Youri N. Lenets

Honeywell Aerospace, Phoenix, AZ

Paper No. GT2012-68736, pp. 157-165; 9 pages
  • ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
  • Volume 7: Structures and Dynamics, Parts A and B
  • Copenhagen, Denmark, June 11–15, 2012
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4473-1
  • Copyright © 2012 by ASME


In an attempt to mitigate future accidents and to harmonize the U.S. and European engine certification requirements, the Federal Aviation Administration (FAA) has recently revised engine certification standards related to the design of engine life-limited parts, also called “critical parts” in European regulations. The updated rule introduces new requirements for engine manufacturers to conduct damage tolerance assessment of all rotating structural parts as well as major static structural parts whose primary failure is likely to result in hazardous engine effects.

Several practical aspects of such damage tolerance assessment, centered on the fatigue crack growth (FCG) testing of aero-GTE materials, are considered in the following. They include, but are not limited to the discussion of the appropriate test specimen geometry and conditions to characterize the behavior of relatively small semi-elliptical cracks emanating from highly stressed surface locations, and fundamental features of the test data analysis. Two novel test approaches — compression pre-cracking and focused ion beam notching — are discussed in detail and associated methodologies developed to study slow FCG and small crack anomalies, respectively, are illustrated by examples.

Copyright © 2012 by ASME
Topics: Fatigue cracks



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