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 buckling (eigenvalue) loads, vibration frequencies, and local stresses. Results show that the scatter in the combined stress is not uniform along the length of the combustor. Furthermore, coefficient of thermal expansion, hoop modulus of the liner material, and the thermal load profile dominate stresses near the support and the intermediate location of the combustor liner. However, the liner thickness, the liner material hoop modulus, and pressure load profile have significant impact on stresses near the free end of combustor.
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ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition
June 5–8, 1995
Houston, Texas, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7882-8
PROCEEDINGS PAPER
Probabilistic Assessment of Combustor Liner Design
Shantaram S. Pai,
Shantaram S. Pai
National Aeronautics and Space Administration Lewis Research Center, Cleveland, OH
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Christos C. Chamis
Christos C. Chamis
National Aeronautics and Space Administration Lewis Research Center, Cleveland, OH
Search for other works by this author on:
Shantaram S. Pai
National Aeronautics and Space Administration Lewis Research Center, Cleveland, OH
Christos C. Chamis
National Aeronautics and Space Administration Lewis Research Center, Cleveland, OH
Paper No:
95-GT-121, V005T14A004; 9 pages
Published Online:
February 16, 2015
Citation
Pai, SS, & Chamis, CC. "Probabilistic Assessment of Combustor Liner Design." Proceedings of the ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award. Houston, Texas, USA. June 5–8, 1995. V005T14A004. ASME. https://doi.org/10.1115/95-GT-121
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