Effect of jet nozzle geometry on flow and heat transfer performance of vortex cooling for gas turbine blade leading edge
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- 作者：Changhe Du ; Liang Li ; liliang@mail.xjtu.edu.cn" class="auth_mail" title="E-mail the corresponding author ; Xin Wu ; Zhenping Feng
- 关键词：Vortex cooling ; Gas turbine blade ; Mechanism ; Aspect ratio ; Area ratio
- 刊名：Applied Thermal Engineering
- 出版年：2016
- 出版时间：25 January 2016
- 年：2016
- 卷：93
- 期：Complete
- 页码：1020-1032
- 全文大小：9965 K
文摘
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We establish a suitable vortex chamber model for gas turbine blade leading edge.
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Mechanism of vortex cooling is further discussed and presented.
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Influences of jet nozzle geometry on vortex cooling characteristics are researched.
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This paper focuses on assessment of flow field and thermal performance for different jet nozzle aspect ratio and area.