Coatings for Rocket Engine Components
Journal of Thermal Spray Technology
Hoboken
RLV thrust cell liner coating analysis and design considerations. This study addresses the relative impact of cooling channel wall and protectiv ethermal coating thickness on the deformation fields of reusable launch vehicle
(RLV) thrust cell liners under in-service loading conditions. The ultima te ob-jective is to identify an optimal liner and coating design that produces st ress and deformation fields leading to improved life/durability. A reference case based on the work of previous studies is introduced, and subsequent changes in geometry and materials are investigated. Analyses are accomplished through the application of the cylindrical version of the higher-order th eory for functionally graded materials/structural components. This theory provides a unique analytical tool for the design of advanced aircraft engine structural components with active cooling channels based on the concept of functionally graded material architectures through which improved deformation and life can be attained. The sensitivity of the cooling channel wall deformation to ch anges in the wall thickness is demonstrated, which is commensurate with the ob-served failure mode. Most importantly, the presence of a NiCrAlY thermal barrier coating is shown to substantially reduce the cooling channel wall dis-tortion.
Keywords: boosters (rocket), boundary conditions, deformation, durability, fi-nite-element method, functionally graded materials, protective coatin gs, ther-mal barrier coatings
D.T. Butler, Jr., J. Aboudi, S.M. Arnold, and M.-J. Pindera, Univ. Virginia,
Charlottesville, VA 22903. Cited: Collection of Technical Papers—AIAA/
ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Con-ference, 7-10 April 2003 (Norfolk, VA), American Inst. Aeronautics and As tro-nautics Inc., pp. 2386-2396 [in English]. ISSN 0273-4508.
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