Numerical Simulation of the Impact of Ratio of Hole Space on Gas-Film Cooling Effectiveness

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Numerical Simulation of the Impact of Ratio of Hole Space on Gas-Film Cooling Effectiveness

更新时间：2025-07-09

- Numerical Simulation of the Impact of Ratio of Hole Space on Gas-Film Cooling Effectiveness
- Vol. 43, Issue 3, Pages: 101-105(2009)
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC： V231.3
- Online First：10 March 2009，
  
  Published：2009
- 稿件说明：
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Numerical Simulation of the Impact of Ratio of Hole Space on Gas-Film Cooling Effectiveness[J]. 2009, 43(3): 101-105.
DOI：

Numerical Simulation of the Impact of Ratio of Hole Space on Gas-Film Cooling Effectiveness[J]. 2009, 43(3): 101-105. DOI：

摘要

为了研究动量比、湍流度和密度比对圆柱形气膜孔流动的影响规律

采用数值模拟方法

研究了圆柱形气膜孔的冷却效率和流量系数

并与实验值进行了对比.结果表明:随着动量比的增大

二次流在气膜孔出口处逐渐偏离叶片; 气膜孔出口下游存在一个高速区域

这一区域的速度随动量比的增大而减小; 在湍流度和密度比保持不变的情况下

随着动量比增加

冷却效率的计算值随着气膜孔中心至测量点的叶片表面长度的增加在总体上呈逐渐减小的趋势; 在低密度比下

湍流度对冷却效率影响不大; 当密度比为1.5时

湍流度的不同导致冷却效率产生显著差异

密度比越小

冷却效率越低; 在气膜孔出口处

冷却效率的数值计算值与实验值存在一定的差异.数值模拟的结果能够定性地反映气膜孔的流动特性.

Abstract

Cooling effectiveness and discharge coefficients of cylindrical gas-film cooling holes were numerically investigated to determine the effects of momentum ratio

density ratio

and turbulence on flow in the holes. The results show that with the increase of momentum ratio

the second flow deviates from the blade at the outlet of the gas-film hole and the velocity in a high velocity zone decreases. Moreover

the cooling effectiveness decreases with the increase of dimensionless length at fixed turbulence and density ratio. In addition

the effect of turbulence on the cooling effectiveness is slight at the low density ratio. The different turbulence causes significant change of the cooling effectiveness and the cooling effectiveness decreases with the decrease of density ratio when density ratio to 1.5. There is an obvious difference between the numerical value and experimental value of the cooling effectiveness at the outlet of the gas-film hole.

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references

韩介勤, 桑地普·杜达, 斯瑞纳斯·艾卡德. 燃气轮机传热和冷却技术[M]. 程代京等,译.西安:西安交通大学出版社, 2005.

刘高文,刘松龄. 涡轮叶栅端壁气膜冷却数值模拟[J]. 推进技术, 2004, 25(2):87-90.

LIU Gaowen,LIU Songling. Numerical simulation of endwall film-cooling in a turbine cascade [J]. Journal of Propulsion Technology,2004,25(2):87-90.

邓明春,朱惠人,李冰,等. 动量比对涡轮叶片气膜孔流量系数的影响 [J]. 燃气涡轮试验与研究, 2006,19(1):35-38.

DENG Mingchun,ZHU Huiren,LI Bing,et al.Influence of momentum ratio on the discharge coefficient of film cooling holes on blade surface in a turbine cascade[J]. Gas Turbine Experiment and Research,2006,19(1):35-38.

刘学强, 伍贻兆. 非结构网格上N-S方程解法研究及在多段翼型绕流中的应用[J]. 空气动力学学报, 2001,19(2):223-227.

LIU Xueqiang,WU Yizhao. Computation of the flow past multi-element airfoils using unstructured grid and N-S equations [J]. Acta Aerodynamica Sinica,2001,19(2):223-227.

JIA Rongguang, BENGT S, MIRON P. A numerical and experimental investigation of the slot film-cooling jet with various angles [J]. ASME Journal of Turbomachinary, 2005, 127(3):635-645.

TASLIN M E, KHANICHEH A. Film effectiveness downstream of a row of compound angle film holes [J]. ASME Journal of Heat Transfer, 2005, 27(4):434-440.

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