NDLI: Finite element analysis of thermal barrier coatings

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Finite element analysis of thermal barrier coatings

Content Provider	NASA Technical Reports Server (NTRS)
Author	Phucharoen, W. Chang, G. C.
Copyright Year	1985
Description	The near-term objective is to develop an understanding of the states of stresses and strains in a Zirconia-yttria thermal barrier coating (TBC) experiencing a given temperature drop. Results so obtained are expected to facilitate experimental work. In order to gain realistic insights into the distribution of stresses and strains in a complex TBC, the finite element approach was selected to model a cylindrical TBC specimen. Experimental evidence reported in the literature indicated the presence of rough interface between the ceramic coat and bond coat. Oxidation of the bond coat at ceramic-bond interface was observed, as was a small amount of cracking in the ceramics near the ceramic-bond interface. To account for these complex features, a plane-strain finite element computer program known as TBCOC was developed, taking advantage of a generic computer code known as MARC. This generic code was made available through the use of a supercomputer (Cray 1). The TBCOC model contains 1316 nodal points and 2140 finite elements. It is capable of a uniform isothermal loading. Results of a sample computer run are presented.
File Size	2853242
Page Count	16
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890004282
Archival Resource Key	ark:/13960/t7mp9x887
Language	English
Publisher Date	1985-01-01
Access Restriction	Open
Subject Keyword	Nonmetallic Materials Finite Element Method Thermal Control Coatings Stress-strain Relationships Stress Distribution Barrier Layers Oxidation Tensile Strength Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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