V肋对尾缘劈缝气膜冷却特性的影响

叶林; 刘存良; 杨寓全; 黄蓉; 朱安冬

doi:10.7527/S1000-6893.2020.24181

航空学报 >

2021 , Vol. 42 >Issue 6: 124181 - 124181

DOI: https://doi.org/10.7527/S1000-6893.2020.24181

流体力学与飞行力学

V肋对尾缘劈缝气膜冷却特性的影响

叶林 ,
刘存良 ,
杨寓全 ,
黄蓉 ,
朱安冬

展开

1. 西北工业大学动力与能源学院, 西安 710072;
2. 西北工业大学陕西省航空动力系统热科学重点实验室, 西安 710129

收稿日期: 2020-05-05

修回日期: 2020-07-13

网络出版日期: 2020-08-31

基金资助

国家自然科学基金（51776173）；西北工业大学博士论文创新基金（CX201913）

收起

Effect of V-shaped ribs on film cooling characteristics of trailing-edge cutback

YE Lin ,
LIU Cunliang ,
YANG Yuquan ,
HUANG Rong ,
ZHU Andong

Expand

1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China;
2. Shaanxi Key Laboratory of Thermal Sciences in Aero-engine System, Northwestern Polytechnical University, Xi'an 710129, China

Received date: 2020-05-05

Revised date: 2020-07-13

Online published: 2020-08-31

Supported by

National Natural Science Foundation of China (51776173); Innovation Foundation for Doctor Dissertation of Northwestern Polytechnical University (CX201913)

Fold

摘要

采用压敏漆技术和瞬态热色液晶技术研究了V肋对尾缘劈缝表面气膜冷却特性的影响，获得了不同吹风比及V肋宽度下2种不同尾缘劈缝表面形状的气膜冷却效率和对流换热系数分布的试验数据，并采用净热流密度值评估对比了带有V肋的劈缝结构的综合冷却性能。试验结果表明：V肋的加入对未扩张型劈缝表面的气膜覆盖产生了不利影响，在小吹风比工况下，V肋宽度对面积平均气膜冷却效率无明显影响，相同V肋宽度结构下，未扩张型劈缝表面的气膜冷却效率始终高于扩张型劈缝表面的；V肋宽度对劈缝表面换热强度的影响不明显，V肋在未扩张劈缝表面结构上展现出的强换热性优于扩张型劈缝表面结构；带有V肋的尾缘劈缝冷却结构可有效增大6.9%~26.6%的净热流密度值，V肋宽度对其无明显影响，小吹风比工况下宜将V肋应用于未扩张的劈缝表面结构，大吹风比工况下无需考虑劈缝表面形状。

关键词： 尾缘劈缝; V肋; 气膜冷却; 强化换热; 压敏漆技术; 瞬态热色液晶技术

本文引用格式

叶林 , 刘存良 , 杨寓全 , 黄蓉 , 朱安冬 . V肋对尾缘劈缝气膜冷却特性的影响[J]. 航空学报, 2021 , 42(6) : 124181 -124181 . DOI: 10.7527/S1000-6893.2020.24181

Abstract

The influence of the V-shaped ribs on the film cooling characteristics of the trailing-edge cutback is studied using the pressure-sensitive paint technology and the transient thermochromic liquid-crystal technology. The distributions of the film cooling effectiveness and heat transfer coefficients on different cutback surfaces with varying V-shaped rib widths at varying blowing ratios are obtained. The heat flux ratio is adopted to evaluate and compare the overall cooling performance of the turbulated cutback surfaces with V-shaped ribs. The experimental results show that the addition of V-shaped ribs has an adverse effect on the film coverage on the unexpanded surface. At low blowing ratios, the rib width has no significant effect on the area-averaged film cooling effectiveness. For the cases with the same rib width, the film cooling effectiveness of the unexpanded surface is always higher than that of the expanded surface. The effect of the V-shaped rib width on the heat transfer enhancement of the trailing-edge cutback is not obvious. The V-shaped ribs exhibit a stronger heat transfer performance on the unexpanded surface than that on the expanded surface. Compared with the primeval trailing-edge cutback, the net heat flux reduction of the case with V-shaped ribs can significantly increase by a factor of 6.9%-26.6%, and the width has no significant effect on the wall heat flux. At low blowing ratios, it is advisable to use V-shaped ribs on the unexpanded surface, while unnecessary to consider the shape of the trailing-edge cutback at high blowing ratios.

Key words： trailing-edge cutback; V-shaped rib; film cooling; heat transfer enhancement; pressure sensitive paint technique; transient thermochromic liquid-crystal technique

参考文献

[1] 程荣辉, 张志舒, 陈仲光. 第四代战斗机动力技术特征和实现途径[J]. 航空学报, 2019, 40(3):022698. CHENG R H, ZHANG Z S, CHEN Z G. Technical characteristics and implementation of the fourth-generation jet fighter engines[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(3):022698(in Chinese).
[2] 屠敏, 袁耿民, 薛飞, 等. 综合热管理在先进战斗机系统研制中的应用[J]. 航空学报, 2020, 41(6):523629. TU M, YUAN G M, XUE F, et al. Application of integrated thermal management in development of advanced fighter system[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6):523629(in Chinese).
[3] CUNHA F J, DAHMER M T, CHYU M K. Analysis of airfoil trailing edge heat transfer and its significance in thermal-mechanical design and durability[J]. Journal of Turbomachinery, 2006, 128(4):738-746.
[4] CUNHA F J, CHYU M K. Trailing-edge cooling for gas turbines[J]. Journal of Propulsion and Power, 2006, 22(2):286-300.
[5] MARTINI P, SCHULZ A, BAUER H J. Film cooling effectiveness and heat transfer on the trailing edge cutback of gas turbine airfoils with various internal cooling designs[J]. Journal of Turbomachinery, 2006, 128(1):196-205.
[6] WU H, LIU Y S, XU G Q. Measurements of heat transfer and pressure in a trailing edge cavity of a turbine blade[J]. Chinese Journal of Aeronautics, 2013, 26(2):294-308.
[7] SHEN Z Y, XIE Y H, ZHANG D. Experimental and numerical study on heat transfer in trailing edge cooling passages with dimples/protrusions under the effect of side wall slot ejection[J]. International Journal of Heat and Mass Transfer, 2016, 92:1218-1235.
[8] MUKHERJEE D K. Film cooling with injection through slots[J]. Journal of Engineering for Power, 1976, 98(4):556-559.
[9] HORBACH T, SCHULZ A, BAUER H J. Trailing edge film cooling of gas turbine airfoils-Effects of ejection lip geometry on film cooling effectiveness and heat transfer[J]. Heat Transfer Research, 2010, 41(8):849-865.
[10] HORBACH T, SCHULZ A, BAUER H J. Trailing edge film cooling of gas turbine airfoils-External cooling performance of various internal pin fin configurations[J]. Journal of Turbomachinery, 2011, 133(4):041006.
[11] 魏建生, 朱惠人, 张丽, 等. 涡轮叶片尾缘劈缝气膜冷却特性实验研究[J]. 工程热物理学报, 2016, 37(9):1988-1993. WEI J S, ZHU H R, ZHANG L, et al. Experimental investigation on the film cooling characteristics of turbine blade trailing edge cutback[J]. Journal of Engineering Thermophysics, 2016, 37(9):1988-1993(in Chinese).
[12] 王瑞琴, 晏鑫, 何坤. 带肋板尾缘开缝叶片内的流动传热性能研究[J]. 西安交通大学学报, 2020, 54(1):150-161,183. WANG R Q, YAN X, HE K. Investigations of flow and heat transfer performance in a blade with trailing-edge cutback and lands[J]. Journal of Xi'an Jiaotong University, 2020, 54(1):150-161,183(in Chinese).
[13] YUAN H P, ZHU H R, KONG M Z. Effects of blowing ratio measured by liquid crystal on heat transfer characteristics of trailing edge cutback[J]. Chinese Journal of Aeronautics, 2008, 21(6):488-495.
[14] YANG Z F, HU H. An experimental investigation on the trailing edge cooling of turbine blades[J]. Propulsion and Power Research, 2012, 1(1):36-47.
[15] 郭之强, 郑梅, 董威, 等. 表面凸起对机翼热气防冰腔内换热强化的影响[J]. 航空学报, 2017, 38(2):520718. GUO Z Q, ZHENG M, DONG W, et al. Influence of surface convex on heat transfer enhancement of wing hot air anti-icing system[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):520718(in Chinese).
[16] HUANG K N, ZHANG J Z, TAN X M, et al. Experimental study on film cooling performance of imperfect holes[J]. Chinese Journal of Aeronautics, 2018, 31(6):1215-1221.
[17] ZHANG J Z, ZHANG S C, WANG C H, et al. Recent advances in film cooling enhancement:A review[J]. Chinese Journal of Aeronautics, 2020, 33(4):1119-1136.
[18] KRUECKELS J, GRITSCH M, SCHNIEDER M. Design considerations and validation of trailing edge pressure side bleed cooling:GT2009-59161[R]. New York:ASME, 2009.
[19] 杨世铭, 陶文铨. 传热学[M]. 4版. 北京:高等教育出版社, 2006:229-243. YANG S M, TAO W Q. Heat transfer[M]. 4th ed. Beijing:Higher Education Press, 2006:229-243(in Chinese).
[20] 陈大为, 朱惠人, 李华太, 等. 尾迹对涡轮动叶全表面气膜冷却效率的影响[J]. 航空学报, 2019, 40(3):122651. CHEN D W, ZHU H R, LI H T, et al. Effect of unsteady wake on full coverage film cooling effectiveness for a turbine blade[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(3):122651(in Chinese).
[21] 刘存良, 朱惠人, 白江涛, 等. 基于瞬态液晶测量技术的收缩-扩张形孔气膜冷却特性[J]. 航空学报, 2009, 30(5):812-818. LIU C L, ZHU H R, BAI J T, et al. Film cooling characteristics of converging-expanding hole with transient liquid crystal measurement technique[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(5):812-818(in Chinese).
[22] YE L, LIU C L, ZHOU D E, et al. Experimental and numerical investigations on the heat transfer of film cooling with cylindrical holes fed with internal coolant cross flows[J]. Journal of Heat Transfer, 2020, 142(5):052302.
[23] 叶林, 刘存良, 杨寓全. 直肋对扩张型尾缘半劈缝气膜冷却特性影响的实验研究[J]. 推进技术,2020, 41(9):2077-2087. YE L, LIU C L, YANG Y Q. Experimental investigation of effects of straight ribs on film cooling performance of expanded cutback surface for trailing-edge[J]. Journal of Propulsion Technology, 2020, 41(9):2077-2087(in Chinese).
[24] KAYS W, CRAWFORD M. Convective heat and mass transfer[M]. 3rd ed. New York:McGraw-Hill,1993:316.
[25] HOLLOWAY D S, LEYLEK J H, BUCK F A. Pressure-side bleed film cooling:Part II-Unsteady framework for experimental and computational results:GT2002-30472[R]. New York:ASME, 2002.
[26] MURATA A, YANO K, HANAI M, et al. Arrangement effects of inclined teardrop-shaped dimples on film cooling performance of dimpled cutback surface at airfoil trailing edge[J]. International Journal of Heat and Mass Transfer, 2017, 107:761-770.
[27] MURATA A, NISHIDA S, SAITO H, et al. Effects of surface geometry on film cooling performance at airfoil trailing edge:GT2011-45355[R]. New York:ASME, 2011.

Options

文章导航

模态框（Modal）标题

摘要

本文引用格式

Abstract

参考文献