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Journal of Thermal Science

热科学学报

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2024 , Vol. 33 >Issue 1: 172 - 189

DOI: https://doi.org/10.1007/s11630-023-1904-x

Comparative Study on Different Methods for Prediction of Thermal Insulation Performance of Thermal Barrier Coating Used on Turbine Blades

  • ZHANG Zhixin ,
  • ZENG Wu ,
  • ZHANG Xiaodong ,
  • ZENG Yuntao
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  • 1. Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
    2. Key Laboratory of Advanced Energy and Power, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
    3. Innovation Academy for Light-duty Gas Turbine, Chinese Academy of Sciences, Beijing 100190, China
    4. University of Chinese Academy of Sciences, Beijing 100049, China

网络出版日期: 2024-01-16

基金资助

This work has been supported by National Science and Technology Major Project (Grand No. J2019-IV-0006-0074) and National Science and Technology Major Project (Grand No. J2019-II-0010-0030).

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Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
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Comparative Study on Different Methods for Prediction of Thermal Insulation Performance of Thermal Barrier Coating Used on Turbine Blades

  • ZHANG Zhixin ,
  • ZENG Wu ,
  • ZHANG Xiaodong ,
  • ZENG Yuntao
Expand
  • 1. Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
    2. Key Laboratory of Advanced Energy and Power, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
    3. Innovation Academy for Light-duty Gas Turbine, Chinese Academy of Sciences, Beijing 100190, China
    4. University of Chinese Academy of Sciences, Beijing 100049, China

Online published: 2024-01-16

Supported by

This work has been supported by National Science and Technology Major Project (Grand No. J2019-IV-0006-0074) and National Science and Technology Major Project (Grand No. J2019-II-0010-0030).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
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摘要

对于带有热障涂层的涡轮叶片，快速且准确的评估其温度分布具有非常重要的意义，尤其是在设计阶段。基于不同程度的简化，诸如是否考虑热障涂层厚度对流道尺寸的改变、是否考虑热障涂层的面内导热等，研究人员在采用流热耦合方法评估带热障涂层的涡轮叶片基体温度分布的时候，提出并采用了3种方法来模拟热障涂层。然而，在上述3种方法对温度评估结果的影响方面，尚未看到公开的研究和探讨。因此，本文设计了3种几何模型，以对上述3种热障涂层模拟方法开展对比研究。第1种几何模型是一个固体导热模型，模型包含基体层和热障涂层。第2种几何模型是一个带有内部冷却和热障涂层的跨音叶栅。第3种几何模型是一个带有圆柱气膜孔和热障涂层的平板气膜冷却模型。结果显示，对于本文中的固体导热模型，在相同的热障涂层表面温度下，3种模拟方法得到的涂层基体界面区的温度分布差异在工程上可忽略不计。对于带内部冷却和热障涂层的跨音叶栅，考虑涂层真实厚度的模拟方法与忽略其真实厚度的2种模拟方法对比，涂层基体界面局部高温点的最大温度差异出现在尾缘位置。前缘位置处的差异小于2K。对于平板气膜冷却模型，不同模拟方法下的展向平均温度的差异可达6K，其主要原因是热障涂层改变了气膜孔的长径比。如果在考虑热障涂层真实厚度的情况下，将基体厚度相应减少以保持气膜孔长径比不变，那么3种模拟方法得到的结果差异则可以忽略。

关键词： turbine blade; thermal barrier coating; conjugate heat transfer; film cooling hole

本文引用格式

ZHANG Zhixin , ZENG Wu , ZHANG Xiaodong , ZENG Yuntao . Comparative Study on Different Methods for Prediction of Thermal Insulation Performance of Thermal Barrier Coating Used on Turbine Blades[J]. 热科学学报, 2024 , 33(1) : 172 -189 . DOI: 10.1007/s11630-023-1904-x

Abstract

As turbine inlet temperature gets higher and higher, thermal barrier coating (TBC) is more and more widely used in turbine blades. For turbine blades with TBC, it is of great significance to evaluate the temperature distribution of its substrate metal quickly and accurately, especially during the design stage. With different degrees of simplification such as whether to consider the change of the geometric size of the fluid domain by TBC and whether to consider the planar heat conduction in TBC, three different methods used in conjugate heat transfer (CHT) simulation to model the TBC of the turbine blades have been developed and widely used by researchers. However, little research has been conducted to investigate the influence of the three methods on the temperature distribution of turbine blade. To fill this gap, three geometric models were designed. They are a solid conduction model with a substrate metal layer and a TBC layer, a transonic turbine vane with internal cooling and TBC, and a plate cylindrical film hole cooling model with TBC. Different methods were used in these geometric models and their differences were carefully analyzed and discussed. The result shows that for the conduction model used in this paper, with the same TBC surface temperature distribution, the difference between the three methods is very small and can be ignored. For a transonic turbine vane with internal cooling, regarding the local maximum temperature of the substrate-TBC interface, the largest difference between the method in which TBC is considered as a thermal resistance or a virtual layer of cells and the method in which three-dimensional heat conduction equation of TBC is solved occurs at the trailing edge. The difference near the leading edge is below 2 K. When employed to the film cooling model, the difference of the laterally averaged temperature of the substrate-TBC interface can be 8 K which is mainly due to the change of the length to diameter ratio of the film cooling hole by TBC. If the substrate thickness is reduced by the thickness of TBC when three-dimensional heat conduction equation of TBC is solved, the temperature difference between the three methods will be quite limited.

Key words： turbine blade; thermal barrier coating; conjugate heat transfer; film cooling hole

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