| LIU Jian-hua 1, LIU Yong-bao 1, HE Xing 1, YU You-hong1, LIU li2.Analyzing of Thermal Insulation of Thermal Barrier Coatings of a Turbine Vane[J].航空发动机,2017,43(4):1-6 |
| Analyzing of Thermal Insulation of Thermal Barrier Coatings of a Turbine Vane |
| DOI： |
| Key Words:thermal barrier coatings temperature field thermal insulation sensitivity曰high pressure turbine曰guide vane |
| Author Name | Affiliation | E-mail | | LIU Jian-hua 1, LIU Yong-bao 1, HE Xing 1, YU You-hong1, LIU li2 | 1. Power Eng. College, Naval University of Engineering, Wuhan 430033, China
2. College of Physics Science and Engineering Technology, Yichun University, Yichun, Jiangxi, 336000,China | yongbaoliu@aliyun.com |
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| Abstract:In order to obtain the insulation properties of the turbine vane thermal barrier coating at the vane flow field. A model of a
turbine vane with Thermal Barrier Coatings (TBCs) was built on. The thermal insulation of TBCs as well as the impacts of Top Coating (TC)
thickness and inlet gas temperature was studied by the conjugate heat transfer method. It was found that the TBCs insulation effects
achieved the maximum value at the suction side of the vane and the minimum value at the tail. And along the flow direction, the insulation
effects increased gradually. Although the surface temperature of TC was variable, the temperature decline along TBCs thickness was
independent on the surface temperature, and the temperature decline ratio got the maximum value at the suction side and the minimum
value at the tail. Every 0.1mm thickening of TC can get about 30益drop of the average temperature of substrate alloy. Additionally the
thermal insulation of TBCs was sensitive to the inlet temperature of gas, and it exhibited linear relationship versus the indexes of
temperature decline of the substrate alloy |
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