Thermal barrier coating life prediction model development.
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Thermal barrier coating life prediction model development.

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Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English

Subjects:

  • Aerodynamic heating.

Book details:

Edition Notes

StatementS.M. Meier, D.M. Nissley, and K.D. Sheffler.
Series[NASA contractor report] -- NASA CR-189111., NASA contractor report -- NASA CR-189111.
ContributionsNissley, D. M., Sheffler, Keith D., United States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL14692478M

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Thermal barrier coating life prediction model development: phase 1. Final report. xviii, (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors / Contributors: J T DeMasi; K D Sheffler; Milton Ortiz; Lewis Research Center. Get this from a library! Thermal barrier coating life prediction model development: final report. [R V Hillery; United States. National Aeronautics and Space Administration.;]. Get this from a library! Thermal barrier coating life prediction model development. Phase II, Final report. [S M Meier; D M Nissley; Keith D Sheffler; United . Abstract A life prediction model for correlating the spallation life of ceramic thermal barrier coatings is developed which includes both cyclic and time-dependent damage. The cyclic damage is.

  1. Introduction. Hot sections of a gas turbine such as turbine blades, vanes, and the combustion chamber liners are safeguarded with thermal barrier coatings (TBCs) [,,,, ].These TBCs have a two-layer structure with a metallic MCrAlY type bond coat (BC) and a ceramic 8 wt% yttria-stabilized zirconia (YSZ) top coat (TC). THERMAL BARRIER COATING LIFE PREDICTION MODEL DEVELOPMENT* R.V. Hillery, B.H. Pilsner, E.C. Duderstadt General Electric Aircraft Engine Business Group The objectives of this program are to determine the predominant modes of degradation of a plasma sprayed thermal barrier coating system, and then to.   A widely used method to produce thermal barrier coating (TBC) systems is the vacuum plasma spraying of a highly dense bondcoat layer with a defined surface roughness and the atmospheric plasma spraying (APS) of a porous (10–15%) Y 2 O 3-stabilized zirconia top thermal cycling operation these systems often fail by crack initiation and propagation close to the bondcoat–top coat.   , S.E. Stewart, M. Ortiz “Thermal barrier coating life prediction model development”. Journal of Engineering for Gas Turbines and .

Get this from a library! Thermal barrier coating life prediction model development: first annual report. [T E Strangman; J Neumann; United States. National Aeronautics and Space Administration.]. The objectives of this program are to increase understanding of thermal barrier coating (TBC) degradation and failure modes, to generate quantitative ceramic failure life data under cyclic thermal conditions which simulate those encountered in gas turbine engine service, and to develop an analytical methodology for prediction of coating life in the engine. Thermal barrier coating life prediction model development. a coating life prediction model was developed based on the data from Task 1 experiments, results from thermomechanical experiments performed as part of Task 2, and finite element analyses of the TBC system during thermal cycles. The third and final task attempted to verify the.   Thermal barrier coatings (TBCs), which offer excellent properties in terms of high-temperature operating, thermal barrier and flow- and wear-resistance, have been developed for application in hot-section components of gas turbines. Research in this area has become a new direction in the surface engineering field.