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Quantification of Thermal-Structural Uncertainties in Engine Combustor Composite Liners FREE

[+] Author Affiliations
Shantaram S. Pai, Christos C. Chamis

National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH

Paper No. 97-GT-108, pp. V004T14A024; 7 pages
doi:10.1115/97-GT-108
From:
  • ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award
  • Orlando, Florida, USA, June 2–5, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7871-2
  • Copyright © 1997 by ASME

abstract

A typical hot structural component within an engine such as composite combustor liner is computationally simulated and probabilistically evaluated in view of the numerous uncertainties associated with the structural, material, and thermo-mechanical load variables (primitive variables) that describe the combustor. The combustor is evaluated for local stresses. Results show that the scatter in the combined stress near the support is significantly dependent upon the uncertainties in the through thickness thermal gradients, the liner material thickness, the coefficient of thermal expansion, and the axial and both the axial and shear moduli.

Copyright © 1997 by ASME
This article is only available in the PDF format.

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