Thermal Mechanical Crack Growth Rate of a High Strength Nickel Base Alloy

[+] Author and Article Information
D. A. Wilson

Dept. of Mechanical Engineering, Tennessee Technological University, Cookeville, TN

J. R. Warren

Pratt & Whitney Aircraft Group, Engineering Division—Florida Operations, West Palm Beach, FL

J. Eng. Gas Turbines Power 108(2), 396-402 (Apr 01, 1986) (7 pages) doi:10.1115/1.3239918 History: Received December 17, 1984; Online October 15, 2009


An understanding of thermal mechanical fatigue (TMF) crack propagation is fundamental to the application of fracture mechanics to gas turbine components. Typical operating conditions for a cooled turbine disk rim consist of a complex mechanical history and an associated variable amplitude thermal history. While thermally induced stress gradients are commonly incorporated in the mechanical history, the effects of thermal cycling on crack growth must be addressed in an appropriate fatigue model. A current computer-based empirical crack propagation modeling system has demonstrated effectiveness under isothermal conditions and can be readily expanded to include thermal-mechanical effects. The existing isothermal models were developed from an extensive data base and describe crack growth over a broad range of temperature and loading conditions. Building on this established system, a model of thermal-mechanical crack growth is being developed.

Copyright © 1986 by ASME
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In