Effect of the shape of divider wall on heat transfer and flow resistance characteristic of passage
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Effect of the shape of divider wall on heat transfer and flow resistance characteristic of passage
Vol. 26, Issue 9, (2011)
作者机构:
1. 北京航空航天大学 能源与动力工程学院 航空发动机气动热力国家级重点实验室,北京,100191
2. 华北电力大学 能源动力与机械工程学院,北京,102206
作者简介:
基金信息:
DOI:
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Published:2011
稿件说明:
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LI Li, XU Guo-qiang, DING Shui-ting, et al. Effect of the shape of divider wall on heat transfer and flow resistance characteristic of passage[J]. 2011, 26(9).
DOI:
LI Li, XU Guo-qiang, DING Shui-ting, et al. Effect of the shape of divider wall on heat transfer and flow resistance characteristic of passage[J]. 2011, 26(9).DOI:
Effect of the shape of divider wall on heat transfer and flow resistance characteristic of passage
Numerical simulation was performed to obtain heat transfer and flow resistance characteristics in a channel with zigzag divider wall in the trailing edge passage of turbine blade.One traditional divider wall and three configurations of zigzag divider walls with different angles were applied to research the effect of angle on the heat transfer and flow resistance.The calculated results indicate that the heat transfer is improved with decrease of the angle of the zigzag shape.For the first passage
the highest improvement was nearly 30 percent.At the same time
the passage with small angle divider wall encountered bigger flow resistance.By comparison of integrated effect of heat transfer
the configurations with smaller angle divider walls have higher values than those with larger angle divider walls.
Experimental investigation of heat transfer and flow resistance in a crossed-rib channel
Experiment of heat transfer in internal cooling channel with tip and trailing edge outflows
Numerical simulation of flow and heat transfer in internal cooling blade channel with leading-edge
Experimental investigation on heat transfer in complex internal cooling blade channel with leading-edge
Influence of orientation angles of branch hole on film cooling effectiveness with one inlet and double outlet hole injection
Related Author
DING Shui-ting
QIN Ling
DENG Hong-wu
TAO Zhi
XU Guo-qiang
LIN Yu-zhen
LIANG Wei-ying
ZHU Hui-ren
Related Institution
National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
School of Power and Energy, Northwestern Polytechnical University,Xian
Liaoning Key Laboratory of Digital Technology Simulation and Test Technique, College of Power and Energy Engineering, Shenyang Aerospace University
Liaoning Key Laboratory of Digital Technology Simulation and Test Technique, School of Aero Dynamics and Energy Engineering, Shenyang Aerospace University
Liaoning Key Laboratory of Digital Technology Simulation and Test Technique,School of Aero Dynamics and Energy Engineering,Shenyang Institute of Aeronautical Engineering