Experimental Research on the Effect of Hole-Inclined Angle on the Film Cooling Characteristics under High Mainstream Turbulence Intensity

doi:10.7652/xjtuxb201801008

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Experimental Research on the Effect of Hole-Inclined Angle on the Film Cooling Characteristics under High Mainstream Turbulence Intensity

更新时间：2025-07-09

- Experimental Research on the Effect of Hole-Inclined Angle on the Film Cooling Characteristics under High Mainstream Turbulence Intensity
- Vol. 52, Issue 1, Pages: 47-53+60(2018)
- 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：10.7652/xjtuxb201801008
  CLC： V231.3
- Online First：10 January 2018，
  
  Published：2018
- 稿件说明：
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Experimental Research on the Effect of Hole-Inclined Angle on the Film Cooling Characteristics under High Mainstream Turbulence Intensity[J]. 2018, 52(1): 47-53+60.
DOI：

Experimental Research on the Effect of Hole-Inclined Angle on the Film Cooling Characteristics under High Mainstream Turbulence Intensity[J]. 2018, 52(1): 47-53+60. DOI： 10.7652/xjtuxb201801008.

摘要

为了研究高湍流度下圆柱孔流向倾斜角对气膜冷却特性的影响

在主流湍流度为11.82%的工况下

采用瞬态热色液晶测量技术对倾斜角为30°、60°的气膜孔冷却特性进行了研究

并与低湍流度工况下的结果进行对比。实验结果表明:气膜孔倾斜角增大会导致气膜冷却效率下降; 主流湍流度增大会提高上游冷却效率

降低下游冷却效率

冷却效率展向分布更加均匀。吹风比的增加导致各倾斜角气膜孔换热系数比显著增加

在小吹风比条件下

换热系数比沿流向时降低

而大吹风比条件下换热系数比呈现先上升后下降的分布; 气膜孔倾斜角增大会在整体上强化壁面对流换热强度

主流湍流度增加导致换热系数比明显减小。随着吹风比的增加

下游区域的主流湍流度导致两种倾斜角气膜孔的冷却效率和换热系数比差距增大

在上游区域主流湍流度的影响较为复杂。

Abstract

To study the influence of inclined angle on the film cooling characteristics under high mainstream turbulence intensity

cylindrical holes with inclined angles 30° and 60° were studied using the transient liquid crystal measurement technique under high mainstream turbulence intensity(11.82%)

and the result was compared with the result under low mainstream turbulence intensity. The results indicate that the film cooling effectiveness decreases with the increase of inclined angle. With the increase of mainstream turbulence intensity

the film cooling effectiveness increases in upstream region and decreases in downstream region

and in addition

the film cooling effectiveness distributes more uniform in the lateral direction. With the increase of blowing ratio

the heat transfer ratio is enhanced obviously for all cylindrical holes. At small blowing ratio

the heat transfer coefficient ratio decreases gradually along the flowing direction. And the heat transfer coefficient ratio has an undulation feature at large blowing ratios. The increase of the inclined angle leads to an enhancement of heat transfer intensity at the same blowing ratio. But the increase of the mainstream turbulence intensity may result in lower heat transfer intensity at the same blowing ratio. With the increase of blowing ratio

the mainstream turbulence intensity-induced differences of the film cooling parameters between two kinds of inclined-angle holes grow under two mainstream turbulence intensities in downstream region

while the influence of mainstream turbulence intensity is more complex in upstream region.

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references

BALDAUF S, SCHEURLEN M, SCHULZ A, et al. Correlation of film cooling effectiveness from thermographic measurements at engine-like conditions [J]. ASME Journal of Turbomachinery, 2002, 124(4): 686-698.

SINHA A K, BOGARD D G, Crawford M E. Film-cooling effectiveness downstream of a single row of holes with variable density ratio [J]. ASME Journal of Turbomachinery, 1991, 113(3): 441-449.

KOHLI A, BOGARD D G. Turbulent transport in film cooling flows [J]. ASME Journal of Heat Transfer, 2005, 127(5): 513-520.

GRITSCH M, SCHULZ A, WITTIG S. Adiabatic wall effectiveness measurements of film-cooling holes with expanded exits [J]. ASME Journal of Turbomachinery, 1998, 120(3): 549-556.

BURD S W, KASZETA R W, SIMON T W. Measurements in film cooling flows: hole L/D and turbulence intensity effects [J]. ASME Journal of Turbomachinery, 1998, 120: 791-798.

LIGRANI P M, WIGLE J M, CIRIELLO S, et al. Film cooling from holes with compound angle orientations: part I Results downstream of two staggered rows of holes with 3D span wise spacing [J]. ASME Journal of Turbomachinery, 1994, 116(2): 242-252.

YUE C H N, MARTINE-BOTAS R F. Film cooling characteristics of single round hole at various stream wise angle in a crossflow: part I Effectiveness [J]. International Journal of Heat and Mass Transfer, 2003, 46(2): 221-235.

AMES F E. Aspects of vane film cooling with high turbulence: part I Heat transfer [J]. Journal of Turbomachinery, 1998, 120(4): 768-776.

AMES F E. Aspects of vane film cooling with high turbulence: part II Adiabatic effectiveness [J]. Journal of Turbomachinery, 1998, 120(4): 777-784.

李广超, 朱惠人, 廖乃冰, 等. 气动参数对前缘气膜冷却效率影响的实验 [J]. 航空动力学报, 2008, 23(2): 215-220.

LI Guangchao, ZHU Huiren, LIAO Naibing, et al. Influence of aerodynamic parameters on film cooling effectiveness on the vane leading edge [J]. Journal of Aerospace Power, 2008, 23(2): 215-220.

周志翔, 刘存良, 张宗卫, 等. 主流湍流度对涡轮导向叶片气膜冷却特性影响的实验 [J]. 航空动力学报, 2014, 29(6): 1279-1286.

ZHOU Zhixiang, LIU Cunliang, ZHANG Zongwei, et al. Experiment on effects of mainstream turbulence intensity on film cooling characteristics of turbine vane [J]. Journal of Aerospace Power, 2014, 29(6): 1279-1286.

刘存良, 朱惠人, 白江涛, 等. 基于瞬态液晶全表面测量技术的圆柱形孔气膜冷却特性研究 [J]. 航空动力学报, 2009, 24(9): 1959-1965.

LIU Cunliang, ZHU Huiren, BAI Jiangtao, et al. Experimental research on film cooling characteristics of cylindrical hole with transient liquid crystal measurement technique [J]. Journal of Aerospace Power, 2009, 24(9): 1959-1965.

刘存良, 朱惠人, 白江涛. 收缩-扩张形气膜孔提高气膜冷却效率的机理研究 [J]. 航空动力学报, 2008, 23(4): 512-517.

LIU Cunliang, ZHU Huiren, BAI Jiangtao, Study on the physics of film-cooling effectiveness enhancement by the converging-expanding hole [J]. Journal of Aerospace Power, 2008, 23(4): 512-517.

MOFFAT R J. Describing the uncertainties in experimental results [J]. Experimental Thermal and Fluid Science, 1988, 1(1): 3-17.

LIU C L, LIU J L, ZHU H R, et al. Film cooling sensitivity of laidback fan shape holes to variations in exit configuration and mainstream turbulence intensity [J]. International Journal of Heat Mass Transfer, 2015, 89(10): 1141-1154.

郑达仁,王新军,张峰,等.上游横向间断肋布置方式对气膜冷却性能的影响.2017,51(11):7-13.[doi:10.7652/xjtuxb 201711002]

翟颖妮,刘存良.高主流湍流度下大倾角异型气膜孔冷却特性实验研究.2017,51(7):16-23.[doi:10.7652/xjtuxb201707 003]

李劲劲,何坤,晏鑫,等.透平叶片近前缘端壁处换热性能的研究.2017,51(7):44-50.[doi:10.7652/xjtuxb201707007]

黄琰,晏鑫,何坤,等.压力面侧小翼结构对凹槽叶顶冷却传热性能的影响.2017,51(7):51-56.[doi:10.7652/xjtuxb2017 07008]

费昕阳,王新军,陆海空.平板冲击发散冷却流动与换热特性的数值模拟.2017,51(7):57-61.[doi:10.7652/xjtuxb201707 009]

张超,宋英杰,宋立明,等.涡发生器高度对气膜冷却性能影响的实验研究.2017,51(3):20-26.[doi:10.7652/xjtuxb2017 03004]

黄琰,晏鑫,何坤,等.气膜孔分布对凹槽叶顶传热和冷却性能的影响.2016,50(5):101-107.[doi:10.7652/xjtuxb201605 015]

高炎,晏鑫,李军.燃气透平叶片尾缘开缝结构冷却性能的数值研究.2016,50(3):29-37.[doi:10.7652/xjtuxb201603005]

周骏飞,王新军,张峰.连续收缩扩张气膜孔排冷却特性的数值模拟.2016,50(3):38-44.[doi:10.7652/xjtuxb201603006]

谢金伟,王新军,周骏飞.空心静叶汽膜孔排吹扫除湿的数值研究.2015,49(7):61-66.[doi:10.7652/xjtuxb201507011]

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Related Institution

西安建筑科技大学机电工程学院

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