Numerical investigation on the influences of impingement holes on heat transfer of leading edge in lamilloy

WANG Ming; LU Yuan-li; JI Hong-hu

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Numerical investigation on the influences of impingement holes on heat transfer of leading edge in lamilloy

更新时间：2026-07-07

- Numerical investigation on the influences of impingement holes on heat transfer of leading edge in lamilloy
- Vol. 28, Issue 10, (2013)
- 作者机构：
  
  1. 中国航空工业集团公司沈阳发动机设计研究所,沈阳,110015
  2. 南京航空航天大学能源与动力学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2013
- 稿件说明：
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WANG Ming, LU Yuan-li, JI Hong-hu. Numerical investigation on the influences of impingement holes on heat transfer of leading edge in lamilloy[J]. 2013, 28(10).
DOI：

WANG Ming, LU Yuan-li, JI Hong-hu. Numerical investigation on the influences of impingement holes on heat transfer of leading edge in lamilloy[J]. 2013, 28(10). DOI：

摘要

根据典型涡轮导向叶片型面和边界条件

对简化的层板冷却叶片前缘的流动和传热特性进行数值研究.考察了两种冲击孔与气膜孔和扰流柱的孔阵排布方式、两种冲击孔轴线与靶面的夹角设置方式对叶片前缘换热的影响

计算中采用re-normalization group(RNG)k-ε湍流模型.结果表明:在气膜孔、扰流柱排布一定的条件下

不同冲击孔的模型的冷却流量相差不到1%.冲击孔数目越多和孔径越小的模型的靶面表面传热系数越高;叶片前缘表面的冷却效率越高

提高约2%.在同一种冲击孔孔阵排布方式下

冲击孔轴线和靶面的夹角对流阻和叶片前缘的换热影响不大.

Abstract

According to the typical guide vane shape and the boundary conditions

numerical investigation was carried out to study the flow and heat transfer characteristics on simplified vane leading edge in lamilloy. Two arrangements of impingement holes

film holes and pin-fins

and two axis modes of impingement holes were analyzed

and re-normalization group(RNG)k-ε turbulent model was used. The results show that with the same arrangement of film holes and pin-fins

the models with different impingement holes have less than 1% of cooling flow rate varies. Besides

the model with more impingement holes and smaller diameter of impingement holes can achieve higher heat transfer coefficient and cooling effectiveness

by about 2%. The angle of impingement holes axis has little influence on heat transfer of leading edge in the same arrangement impingement holes.

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