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In-Situ Study on Coaxing During Vibration-Based Bending Fatigue of Inconel 625 and 718

[+] Author Affiliations
Onome Scott-Emuakpor, Jeremy Schwartz, Tommy George, Charles Cross

Air Force Research Laboratory, Wright-Patterson AFB, OH

Casey Holycross, M. H. Herman Shen

The Ohio State University, Columbus, OH

Paper No. GT2013-94233, pp. V07AT27A003; 9 pages
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 7A: Structures and Dynamics
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5526-3
  • Copyright © 2013 by ASME


This study observes coaxing effects on aerospace nickel alloys during vibration-based bending fatigue loading. The purpose of this analysis is to determine if Goodman diagrams can be constructed using bending fatigue life data at experimentally defined cycles to failure. The methodology for controlling the number of cycles to failure requires a series of understressing steps, where stress amplitude is incrementally increased at each step. This method, known as the step-test procedure, states that, for some materials, the stress amplitude corresponding to the controlled cycles-to-failure can be determined through linear interpolation between the failure step and the previous non-failure step. Using the step-test procedure, experimental bending fatigue life results were gathered from cold-rolled Inconel 625 and 718 plate specimens. These bending loads are applied with a vibration-based experimental method, known as the George fatigue method, which utilizes modal vibration for fatigue loading. The fatigue life results from the George fatigue method are compared to life data from previously published constant stress amplitude experiments to determine if coaxing affects the fatigue performance of the Inconel materials. Results show that Inconel 625 has an improved fatigue performance that could be attributed to several possible factors, including coaxing, while the Inconel 718 data is shown to be within a 50% confidence band of constant stress amplitude data from the same material stock. The findings in this study increases the knowledge necessary to attain more relevant and less conservative empirical data for designing against high cycle fatigue (HCF) failure of complex gas turbine engine components.

Copyright © 2013 by ASME
Topics: Fatigue , Vibration



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