Stress Analysis for Plasma Sprayed Thermal Barrier Coating on the Turbine Vane

TANG  Jiapeng; LI  Zhiyong

doi:10.15892/j.cnki.djzdxb.2010.06.004

Journal of Projectiles, Rockets, Missiles and Guidance >

2010 , Vol. 30 >Issue 6: 227 - 229

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2010.06.004

CORRELATION TECHNOLOGY

Stress Analysis for Plasma Sprayed Thermal Barrier Coating on the Turbine Vane

TANG Jiapeng ,
LI Zhiyong

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¹ School of Mechatronics Engineering, North University of China, Taiyuan 030051,China
² Beijing University of Aeronautics and Astronautics, Beijing 100083,China

Received date: 2010-03-27

Online published: 2025-05-28

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Abstract

According to the characteristics of the plasma sprayed thermal barrier coating on the aero engine turbine vane under differ-ent conditions, structure and finite element model of the vane were established. Thermal barrier coating was analyzed by Marc soft-ware systematically. The stress changes in the coating under different temperature and oxide thickness were calculated separately. The failure characteristics of the thermal barrier coating and the effect characteristics of its factors were learned.

Key words： turbine vane; finite element; thermal barrier coating; residual stress

Cite this article

TANG Jiapeng , LI Zhiyong . Stress Analysis for Plasma Sprayed Thermal Barrier Coating on the Turbine Vane[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2010 , 30(6) : 227 -229 . DOI: 10.15892/j.cnki.djzdxb.2010.06.004

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