Numerical investigation on influence of thermal barrier coatings on turbine blade

王利平

doi:10.3969/j.issn.0438-1157.2012.z1.024

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Numerical investigation on influence of thermal barrier coatings on turbine blade

更新时间：2025-12-10

- Numerical investigation on influence of thermal barrier coatings on turbine blade
- CIESC Journal Issue S1, Pages: 130-137(2012)
- 作者机构：
  
  南京航空航天大学能源与动力学院,江苏,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.3969/j.issn.0438-1157.2012.z1.024
  CLC： 231.1
- Online First：28 May 2012，
  
  Published：28 May 2012
- 稿件说明：
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王利平. Numerical investigation on influence of thermal barrier coatings on turbine blade[J]. CIESC Journal, 2012, (S1): 130-137.
DOI：

王利平. Numerical investigation on influence of thermal barrier coatings on turbine blade[J]. CIESC Journal, 2012, (S1): 130-137. DOI： 10.3969/j.issn.0438-1157.2012.z1.024.

摘要

以带有复合冷却结构的涡轮叶片为基础模型，对有/无热障涂层保护下的叶片冷却效果进行了气热耦合数值计算，并通过改变热障涂层的厚度研究了热障涂层对叶片换热的影响规律。研究发现：带有热障涂层的叶片温度明显下降，且越靠近叶片前缘处，温度降低幅度越大；随着热障涂层厚度的增加，下降趋势逐渐变慢；与无热障涂层时叶片温度相比，叶片前缘区域温降最大，当热障涂层厚度为0.35mm时，温降高达160K，压力面和吸力面与前缘相比温降程度较低。

Abstract

The influence of thermal barrier coatings with different thicknesses on turbine blade with internal cooling was investigated using the numerical computation method of conjugate heat transfer.The results show that the temperature of the turbine blade with thermal barrier coatings decreases demonstrably，and the decrease of temperature got much more when approaching to the leading face.The falling speed was slower with the creasing of the thickness of thermal barrier coatings.The leading face has the largest decrease of temperature which was 160K when the thickness of thermal barrier coatings was 0.35mm.

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Related Institution

Key Laboratory of Thermo-Fluid Science and Engineering, Ministry of Education, Xi’an Jiaotong University, , Shaanxi

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