Experiments of flow and heat transfer performances for air-cooling laminated turbine vane

WU Xiang-yu; TAO Zhi; DU Zhi-neng; ZHANG Shu-lin; YOU Hong-de

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Experiments of flow and heat transfer performances for air-cooling laminated turbine vane

燃烧、传热、传质 | 更新时间：2026-07-07

- Experiments of flow and heat transfer performances for air-cooling laminated turbine vane
- Experiments of flow and heat transfer performances for air-cooling laminated turbine vane
- 航空动力学报 2014年第5期
- 作者机构：
  
  1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics,Beijing,China,100191
  2. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China,Shenyang,China,110015
- 作者简介：
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- 纸质出版：2014
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WU Xiang-yu, TAO Zhi, DU Zhi-neng, 等. Experiments of flow and heat transfer performances for air-cooling laminated turbine vane[J]. 航空动力学报, 2014,(5).

WU Xiang-yu, TAO Zhi, DU Zhi-neng, et al. Experiments of flow and heat transfer performances for air-cooling laminated turbine vane[J]. 2014, (5).
WU Xiang-yu, TAO Zhi, DU Zhi-neng, 等. Experiments of flow and heat transfer performances for air-cooling laminated turbine vane[J]. 航空动力学报, 2014,(5). DOI：

WU Xiang-yu, TAO Zhi, DU Zhi-neng, et al. Experiments of flow and heat transfer performances for air-cooling laminated turbine vane[J]. 2014, (5). DOI：

摘要

Flow resistance and heat transfer coefficients of typical double wall laminated film cooling configuration within a turbine vane were experimentally studied. The specimen was in large scale

and made of transparent organic glass. Laminated configuration consisted of double wall laminates

pin-fins

staggered arrays of impingement and film holes. The number ratio of impingement holes

pin-fins and film holes was 2:1:1. Five experiment vanes were installed in static cascade

and experiments were carried out under constant heat flux. Re of internal cooling air in the experiment was from 104 to 2×105

and Re of external fluid was from 105 to 3×105. The experiment results show that flow resistances of front channel and back channel of the vane are in the same level

and both of them decrease as Re of cooling air increases. Nu of front channel is slightly higher than that of back channel. Both of them increase as Re of cooling air increases. And experiment results were obtained from experiment vanes were compared with that obtained from laminated flat plates

and the tendency of the results agrees well.

Abstract

Flow resistance and heat transfer coefficients of typical double wall laminated film cooling configuration within a turbine vane were experimentally studied. The specimen was in large scale

and made of transparent organic glass. Laminated configuration consisted of double wall laminates

pin-fins

staggered arrays of impingement and film holes. The number ratio of impingement holes

pin-fins and film holes was 2:1:1. Five experiment vanes were installed in static cascade

and experiments were carried out under constant heat flux. Re of internal cooling air in the experiment was from 104 to 2×105

and Re of external fluid was from 105 to 3×105. The experiment results show that flow resistances of front channel and back channel of the vane are in the same level

and the tendency of the results agrees well.

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