THERMAL BARRIER COATING LIFE PREDICTION MODEL DEVELOPMENT

被引：125

作者：

MEIER, SM ^{[1
]}

NISSLEY, DM ^{[1
]}

SHEFFLER, KD ^{[1
]}

CRUSE, TA ^{[1
]}

机构：

[1] VANDERBILT UNIV, DEPT MECH ENGN, NASHVILLE, TN 37235 USA

来源：

JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME | 1992年 / 114卷 / 02期

关键词：

D O I：

10.1115/1.2906581

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

A thermal barrier coated (TBC) turbine component design system, including an accurate TBC life prediction model, is needed to realize the full potential of available TBC engine performance and/or durability benefits. The objective of this work, which was sponsored in part by NASA under the Hot Section Technology (HOST) Program (Contract NA S3-23944), was to generate a life prediction model for electron beam-physical vapor deposited (EB-PVD) zirconia TBC. Specific results include EB-PVD zirconia mechanical and physical properties, coating adherence strength measurements, interfacial oxide growth characteristics, quantitative cyclic thermal spallation life data, and a spallation life model.

引用

页码：258 / 263

页数：6

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