Vortex cooling performance in internal cooling channelof turbine blade trailing edge

被引：0

作者：

机构：

[1] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

来源：

Xu, H.-Y. | 1600年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 29期

关键词：

Convection heat transfer; Enhanced heat transfer; Trailing edge; Turbine blade; Vortex cooling;

D O I：

10.13224/j.cnki.jasp.2014.01.008

中图分类号：

学科分类号：

摘要：

Three different kinds of vortex cooling configurations were designed and applied to the simplified blade trailing edge. The cooling air flow was injected into the vortex cavities from jet orifices located at the middle of the vortex cavity, staggered side of the vortex cavity and the inline side of the vortex cavity, respectively. A comparison with the common cooling channel fitted with bumps and pin fins was made by numerical simulation. The mechanism and effect of enhanced heat transfer were analyzed. Results show that the configuration of vortex flow cavity and the arrangement of cooling air inflow have important influences on the vortex cooling performances. The vortex cooling configurations with the cooling air injected to one side of the vortex cavity causes significant vortex flows not only in the streamwise plane but also in the spanwise plane, which enhances the convection heat transfer. The vortex cooling configuration can enhance heat transfer in comparison with the bumps and pin fins, with the average Nusselt number increasing 6.8%-22.9%. However, the flow resistance also increases. The vortex cooling configuration with the jet orifices located at the staggered side of the vortex cavity enhances heat transfer capacity greatly, and the configuration with the jet orifices located at the inline side of the vortex cavity, of which the comprehensive coefficient of convection heat transfer is 4.2% higher than that of the bumps and pin fins, achieves the best comprehensive performance.

引用

页码：59 / 66

页数：7

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