Hot flowpath components in aircraft gas turbine engines are subject to a severe operating environment. The large thermal gradients can produce high thermal strains that, when combined with mechanical loads and a deleterious environment, can lead to premature failure. To combat this possibility, designers spend considerable time determining the stress and strain fields in these components as the parts undergo typical operating histories. These field quantities can then be used to determine failure parameters and determine life limiting locations. The field determinations can be difficult and, in combination with numerous potential failure mechanisms, the structural assurance process can take a considerable time to complete. To shorten this process, a personal computer (PC) based preliminary design system has been developed. This system, called Thermo-mechanical Fatigue—Structural Life Assessment Method (TMFSLAM), permits the user to rapidly evaluate the interactive effects of duty cycle, geometry, and materials on component life. The quantitative results determined by TMFSLAM will be available to make decisions on design changes, material substitution, etc.
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April 1992
Research Papers
TMFSLAM—Design Analysis Tool for Coated Structures
G. S. Bechtel,
G. S. Bechtel
General Electric Aircraft Engines, Cincinnati, OH 45215
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R. L. McKnight,
R. L. McKnight
General Electric Aircraft Engines, Cincinnati, OH 45215
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T. S. Cook
T. S. Cook
General Electric Aircraft Engines, Cincinnati, OH 45215
Search for other works by this author on:
G. S. Bechtel
General Electric Aircraft Engines, Cincinnati, OH 45215
R. L. McKnight
General Electric Aircraft Engines, Cincinnati, OH 45215
T. S. Cook
General Electric Aircraft Engines, Cincinnati, OH 45215
J. Eng. Gas Turbines Power. Apr 1992, 114(2): 309-314 (6 pages)
Published Online: April 1, 1992
Article history
Received:
February 20, 1991
Online:
April 24, 2008
Citation
Bechtel, G. S., McKnight, R. L., and Cook, T. S. (April 1, 1992). "TMFSLAM—Design Analysis Tool for Coated Structures." ASME. J. Eng. Gas Turbines Power. April 1992; 114(2): 309–314. https://doi.org/10.1115/1.2906588
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