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Structural analysisHot section components of aircraft gas turbine engines are subjected to severe thermal-structural loading conditions, especially during the start-up and take-off portions of the engine cycle. The most severe and damaging stresses and strains are those induced by the steep thermal gradients induced during the start-up transient. These transient stresses and strains are also the most difficult to predict, in part because the temperature gradients and distributions are not well known or predictable, and also because the cyclic elasto-viscoplastic behavior of the materials at these extremes of temperature and strain are not well known or predictable. One element of the structures program will develop improved time-varying thermal-mechanical load models for the entire engine mission cycle from start-up to shutdown. The thermal model refinements will be consistent with those required by the structural code including considerations of mesh-point density, strain concentrations, and thermal gradients. Models will be developed for the burner liner, turbine vane and turbine blade.
Document ID
19850002661
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johns, R. H.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1982
Publication Information
Publication: Turbine Eng. Hot Sect. Technol. (HOST)
Subject Category
Aircraft Propulsion And Power
Accession Number
85N10969
Distribution Limits
Public
Copyright
Public Use Permitted.
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