高主流湍流度下大倾角异型气膜孔冷却特性实验研究

翟颖妮 1; 刘存良 2

doi:10.7652/xjtuxb201707003

您当前的位置：

首页 >

文章列表页 >

高主流湍流度下大倾角异型气膜孔冷却特性实验研究

更新时间：2025-07-09

- 高主流湍流度下大倾角异型气膜孔冷却特性实验研究
- Experimental Study on the Film Cooling Performance of Odd-Shaped Film Holes with Large Inclination Angle under High Turbulence Intensity
- 西安交通大学学报 2017年51卷第7期页码：16-23
- 作者机构：
  
  西安建筑科技大学机电工程学院,西安,710055
- 作者简介：
- 基金信息：
  
  : 2017-01-23。作者简介: 翟颖妮(1983—),女,博士,讲师。基金项目: 陕西省自然科学基础研究计划资助项目(2016JQ5056);国家自然科学基金资助项目(51306152)
- DOI：10.7652/xjtuxb201707003
  中图分类号： V231.3
- 网络首发：2017-07-10，
  
  纸质出版：2017
- 稿件说明：
移动端阅览
翟颖妮 1, 刘存良 2. 高主流湍流度下大倾角异型气膜孔冷却特性实验研究[J]. 西安交通大学学报, 2017,51(7):16-23.

Experimental Study on the Film Cooling Performance of Odd-Shaped Film Holes with Large Inclination Angle under High Turbulence Intensity[J]. 2017, 51(7): 16-23.
翟颖妮 1, 刘存良 2. 高主流湍流度下大倾角异型气膜孔冷却特性实验研究[J]. 西安交通大学学报, 2017,51(7):16-23. DOI： 10.7652/xjtuxb201707003.

Experimental Study on the Film Cooling Performance of Odd-Shaped Film Holes with Large Inclination Angle under High Turbulence Intensity[J]. 2017, 51(7): 16-23. DOI： 10.7652/xjtuxb201707003.

摘要

为了研究高主流湍流度下大倾斜角异型气膜孔的冷却特性

在主流湍流度为11.82%的流动工况下

采用瞬态液晶传热测量技术对倾斜角均为60°的圆柱孔、水滴孔以及曲面簸箕孔进行了研究。在吹风比为0.5的工况下

3种孔型的气膜贴壁性都较好

上游冷却效率高于下游; 在吹风比为1.0的工况下

圆柱孔和水滴孔出现气膜脱离壁面再附着现象

上游冷却效率低于下游; 在更大吹风比下

曲面簸箕孔气膜也出现脱离再附着现象。吹风比的增加会显著增强各个气膜孔的对流换热强度

曲面簸箕孔的换热系数比在各个吹风比下都低于圆柱孔和水滴孔

圆柱孔和水滴孔的换热系数比在上游区域较高

而曲面簸箕孔的换热系数比在大吹风比下呈现出先上升后下降的分布特征。实验结果表明

在高主流湍流度条件下

大倾斜角水滴孔和圆柱孔的气膜冷却效果相近

曲面簸箕孔的气膜冷却效果优于这两种孔型。

Abstract

In order to obtain the film cooling characteristics of odd-shaped film holes with large inclination angle under high mainstream turbulence intensity

three film hole configurations with an inclination angle of 60°

including cylindrical hole

water-drop hole and curved dustpan hole

were studied under the mainstream turbulence intensity of 11.82% using transient liquid crystal measurement technique. At a blowing ratio of 0.5

the film attachment behavior on the wall is good for all the three hole configurations

and the film cooling efficiency in upstream region is higher than that in downstream region. At a blowing ratio of 1.0

the film jets lift off from the wall for the cylindrical hole and water-drop hole

resulting in lower film cooling efficiency in upstream region. With further increase of blowing ratio

the film jets of the curved dustpan hole also lift off from the wall. The increase of blowing ratio will obviously enhance the heat transfer intensity for all the three hole configurations. The heat transfer coefficient ratio of the cylindrical hole and water-drop hole decreases gradually along the streamwise direction. And the heat transfer coefficient ratio of the curved dustpan hole is lower than that of the cylindrical hole and water-drop hole under all blowing ratios

and has an undulation feature at large blowing ratios. The above results indicate that the film cooling performance of the curved dustpan hole is better than that of the cylindrical hole and water-drop hole under all blowing ratios

but the film cooling performance of the cylindrical hole and water-drop hole with large inclination angles is close to each other.

关键词

Keywords

references

PETERSEN D R, ECKERT E R G, GOLDSTEIN R J. Filming cooling with large density differences between the mainstream and secondary fluid measured by heat-mass transfer analogy [J]. ASME Journal of Heat Transfer, 1977, 99(4): 620-627.

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.

BUNKER R S. A review of shaped hole turbine film-cooling technology [J]. ASME Journal of Heat Transfer, 2005, 127(4): 441-453.

DITTMAR J, SCHULZ A, WITTIG S. Assessment of various film-cooling configurations including shaped and compound angle holes based on large-scale experiments [J]. ASME Journal of Turbomachinery, 2003, 125(1): 57-64.

GRITSCH M, COLBAN W, SCHAR H. Effect of hole geometry on the thermal performance of fan-shaped film cooling holes [J]. ASME Journal of Turbomachinery, 2005, 127(4): 718-725.

YU Y, YEN C H, SHIH T I P, et al. Film cooling effectiveness and heat transfer coefficient distributions around diffusion shaped holes [J]. ASME Journal of Heat Transfer, 2002, 124(5): 820-827.

BAI J T, ZHU H R, LIU C L. Film cooling characteristic of double-fan shaped film cooling holes [C]∥ASME Turbo Expo 2009: Power for Land, Sea, Air. New York, USA: ASME, 2009: 185-198.

LIU C L, ZHU H R, BAI J T, et al. Film cooling performance of converging-slot holes with different exit-entry area ratios [J]. ASME Journal of Turbomachinery, 2011, 133(1): 011020.

LIU C L, ZHU H R, BAI J T, et al. Experimental and numerical investigation on the film cooling of waist-shaped slot holes comparing with converging slot holes [J]. ASME Journal of Turbomachinery, 2012, 134(1): 011021.

吴阿赛, 朱惠人, 刘存良, 等. 基于热色液晶的异型气膜孔气膜分布特征的可视化实验 [J]. 航空动力学报, 2015, 30(2): 376-383.

WU Asai, ZHU Huiren, LIU Cunliang, et al. Visualization experiment on film distribution characteristics of shaped film holes based on thermochromic liquid crystal [J]. Journal of Aerospace Power, 2015, 30(2): 376-383.

SAUMWEBER C, SCHULZ A, WITTIG S. Free-stream turbulence effects on film cooling with shaped holes [J]. ASME Journal of Turbomachinery, 2002, 125(1): 41-49.

SAUMWEBER C, SCHULZ A. Free-stream effects on the cooling performance of cylindrical and fan-shaped cooling holes [J]. ASME Journal of Turbomachinery, 2012, 134(6): 061007.

WRIGHT L M, MCCLAIN S T, CLEMENSON M D. PIV investigation of the effect of freestream turbulence intensity on film cooling from fanshaped holes [C]∥AMSE Turbo Expo 2011: Turbine Technical Conference and Exposition. New York, USA: ASME, 2011: 493-507.

DITTMAR J, SCHULZ A, WITTIG S. Assessment of various film-cooling configurations including Shaped and compound angle holes based on large-scale experiments [J]. ASME Journal of Turbomachinery, 2003, 125(1): 109-118.

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

YUEN C H N, MARTINEZ-BOTAS R F. Film cooling characteristics of a single round hole at various streamwise angles in a crossflow: part II Heat transfer effectiveness [J]. International Journal of Heat and Mass Transfer, 2003, 46(2): 237-249.

李广超, 朱惠人, 樊慧明. 双向扩张型孔射流角度对气膜冷却特性影响的实验 [J]. 航空动力学报, 2009, 24(5): 1000-1005.

LI Guangchao, ZHU Huiren, FAN Huiming. Experimental investigation on film cooling of expanded hole atboth inlet and outlet with various injection angles [J]. Journal of Aerospace Power, 2009, 24(5): 1000-1005.

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 Zhongwei, 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. 新型高效气膜孔冷却特性研究 [D]. 西安: 西北工业大学, 2009.

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 fanshape holes to variations in exit configuration and mainstream turbulence intensity [J]. International Journal of Heat Mass Transfer, 2015, 89(10): 1141-1154.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

高主流湍流度下倾斜角对圆柱孔气膜冷却特性影响的实验研究

张角凹坑气膜孔对双层壁气膜冷却特性的影响

带肋曲面双层壁偏转内流与传热冷却特性数值研究

涡轮叶栅前缘区域叶片与端壁交互气膜冷却作用数值研究

面向气膜冷效提升的涡轮叶栅全端壁非轴对称造型设计优化