全气膜冷却叶片表面换热系数和冷却效率研究

张宗卫; 朱惠人; 刘聪; 孟庆昆

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全气膜冷却叶片表面换热系数和冷却效率研究

更新时间：2025-07-09

- 全气膜冷却叶片表面换热系数和冷却效率研究
- Heat Transfer Coefficient and Film Cooling Effectiveness on a Full-Film Cooling Vane
- 西安交通大学学报 2012年46卷第7期页码：103-107
- 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：
  
  : 2011-12-13. 作者简介: 张宗卫(1984-),男,博士生;朱惠人(通信作者),男,教授,博士生导师. 基金项目: 国家重点基础研究发展计划资助项目(2007CB707701)
- DOI：
  中图分类号： V231.1
- 网络首发：2012-07-10，
  
  纸质出版：2012
- 稿件说明：
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张宗卫, 朱惠人, 刘聪, 等. 全气膜冷却叶片表面换热系数和冷却效率研究[J]. 西安交通大学学报, 2012,46(7):103-107.

Heat Transfer Coefficient and Film Cooling Effectiveness on a Full-Film Cooling Vane[J]. 2012, 46(7): 103-107.
张宗卫, 朱惠人, 刘聪, 等. 全气膜冷却叶片表面换热系数和冷却效率研究[J]. 西安交通大学学报, 2012,46(7):103-107. DOI：

Heat Transfer Coefficient and Film Cooling Effectiveness on a Full-Film Cooling Vane[J]. 2012, 46(7): 103-107. DOI：

摘要

为了研究全气膜冷却涡轮导叶叶片的换热特性

采用瞬态液晶技术获得了叶片全表面的高分辨率换热系数和冷却效率.实验在三叶片两通道放大模型中完成

叶栅进口雷诺数是1.0×10

.叶片前缘有8排复合角孔

压力面有21排轴向角孔

吸力面有24排轴向角孔.气膜孔排由2个供气腔供气

前腔二次流与主流的质量流量比为4.56%

后腔为4.67%.结果表明:受叶栅通道涡作用

气膜出流在吸力面呈聚敛状

在压力面则呈发散状.气膜出流受气膜孔角度影响

气膜孔下游的换热系数和冷却效率都较高.叶片前缘受到冲击

换热强

冷却效率低; 叶片吸力面冷却效率维持在0.4左右

压力面维持在0.35左右.该全气膜冷却叶片气膜覆盖效果较好

冷却效率和换热系数分布均匀

是一种较好的冷却结构.

Abstract

The high-resolution heat transfer coefficient and the film effectiveness measurements on a full-film cooling nozzle guide vane with compound and axial angle holes were obtained using a transient liquid crystal technique. The tests were performed in a scaled-up

two-passage cascade at an inlet Reynolds number of 1.0×10

. There are eight rows of compound angle cylinder film holes around the leading edge

21 rows of axial angle cylinder holes on the pressure side

and 24 rows of axial angle cylinder holes on the suction side. The holes are fed from two internal plenum with a mass flow ratio of 4.56% in the first plenum and 4.67% in the second plenum. The results show that the film cover region shrinks on the suction side and expands on the pressure side due to the influence of passage vortex. The heat transfer coefficient and the film

cooling effectiveness are higher in the near hole region. The heat transfer coefficient is higher and the film cooling effectiveness is lower near the leading edge. The film cooling effectiveness is about 0.4 on the suction side and about 0.35 on the pressure side

respectively.

关键词

Keywords

references

曹玉璋,陶智,徐国强,等.航空发动机传热学[M].北京:北京航空航天大学出版社,2005:4-15.

NA S, SHIH T I. Increasing adiabatic film-cooling effectiveness by using an upstream ramp [J]. Journal of Heat Transfer, 2007,129(4): 464-471

张宗卫, 朱惠人, 杜小琴, 等. 带60°肋和出流孔的矩形通道端壁换热特性研究[J]. 西安交通大学学报, 2010,44(5):116-119.

ZHANG Zongwei, ZHU Huiren, DU Xiaoqin, et al. Investigations of endwall heat transfer in the rectangular passage with 60-degree ribs and suction holes[J].Journal of Xi'an Jiaotong University, 2010, 44(5): 116-119.

GUO S M, LAI C C, JONES T V, et al. The application of thin-film technology to measure turbine-vane heat transfer and effectiveness in a film-cooled, engine-simulated environment[J]. International Journal of Heat and Fluid Flow, 1998,19(6):594-600.

WAYE S K, BOGARD D G. High-resolution film cooling effectiveness comparison of axial and compound angle holes on the suction side of a turbine vane[J]. Journal of Turbomachinery, 2007,129(2):202-211.

DHUNGEL A, LU Y, PHILLIPS W, et al. Film cooling from a row of holes supplemented with antivortex holes[J]. Journal of Turbomachinery, 2009,131(2):21007-21010.

白江涛, 朱惠人, 张宗卫, 等. 叶片全表面换热系数和冷却效率的实验测量[J]. 西安交通大学学报, 2010, 44(11):92-97.

BAI Jiangtao, ZHU Huiren, ZHANG Zongwei, et al. Measurements of heat transfer coefficient and film cooling effectiveness distribution on a vane using transient liquid crystal technique[J]. Journal of Xi'an Jiaotong University, 2010, 44(11):92-97.

IRELAND P T, JONES T V. Liquid crystal measurements of heat transfer and surface shear stress[J]. Measurement Science and Technology, 2000, 11(7):969-986.

白江涛, 朱惠人, 刘存良. 双参数传热实验的液晶瞬态测量不确定度分析[J]. 航空动力学报, 2009,24(9):1945-1951.

BAI Jiangtao, ZHU Huiren, LIU Cunliang. Analysis of uncertainties in two-parameter transient heat transfer measurements with liquid crystal[J]. Journal of Aerospace Power, 2009, 24(9):1945-1951.

WANG H P, OLSON S J, GOLDSTEIN R J, et al. Flow visualization in a linear turbine cascade of high performance turbine blades[J]. Journal of Turbomachinery, 1997, 119(1):1-8.

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