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Temperature distributions and thermal stresses in a graded zirconia/metal gas path seal system for aircraft gas turbine engines
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Temperature distributions and thermal stresses in a graded zirconia/metal gas path seal system for aircraft gas turbine engines
Temperature distributions and thermal stresses in a graded zirconia/metal gas path seal system for aircraft gas turbine engines
CT
C. Taylor
C. Taylor
RB
R. Bill
R. Bill
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16 January 1978
proceedings article
Published by
American Institute of Aeronautics and Astronautics (AIAA)
https://doi.org/10.2514/6.1978-93
Abstract
No abstract available
Cited by 1 article