基于结构参数分析的姊妹孔气膜冷却性能研究

doi:10.7527/S1000-6893.2020.24775

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

基于结构参数分析的姊妹孔气膜冷却性能研究

王进¹, 孙杰¹, 赵占明¹, 张勃¹, 任晓栋^2,3, 谢公南⁴

1. 河北工业大学能源与环境工程学院, 天津 300401;
2. 清华大学热科学与动力工程教育部重点实验室, 北京 100084;
3. 先进航空发动机协同创新中心, 北京 100191;
4. 西北工业大学航海学院, 西安 710072

收稿日期:2020-09-22 修回日期:2020-10-15 发布日期:2020-12-25
通讯作者: 谢公南 E-mail:xgn@nwpu.edu.cn
基金资助:
国家自然科学基金（51806118，51806057）

Research on film cooling performance of sister hole based on structural parameter analysis

WANG Jin¹, SUN Jie¹, ZHAO Zhanming¹, ZHANG Bo¹, REN Xiaodong^2,3, XIE Gongnan⁴

1. School of Energy and Environmental Engineering, Hebei University of Technology, Tianjin 300401, China;
2. Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Tsinghua University, Beijing 100084, China;
3. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;
4. School of Marine Science and Technology, Northwestern Polytechnical University, Xi'an 710072, China

Received:2020-09-22 Revised:2020-10-15 Published:2020-12-25
Supported by:
National Natural Science Foundation of China (51806118, 51806057)

摘要/Abstract

摘要： 以姊妹孔气膜冷却结构的偏转角度、倾斜角度和吹风比为因素，并以壁面平均气膜冷却效率为评价指标，应用田口方法设计了三因素五水平正交表，并结合数值计算对不同工况下的流场特征和冷却效率分布进行了分析。计算结果表明：高吹风比下姊妹孔冷却效率为常规圆柱孔冷却效率的165%~412.5%，正向10°偏转的姊妹孔冷却效率均大于负向10°偏转的姊妹孔冷却效率。参数化结果表明：吹风比为0.5、偏转角度为10°、倾斜角度为35°的结构表现出最佳冷却效果。

关键词: 姊妹孔, 气膜冷却效率, 田口方法, 吹风比, 偏转角

Abstract: A three-factor and five-level orthogonal table is designed using the Taguchi method for the sister hole structure, with the compound angle, the inclination angle and the blowing ratio as factors and the average wall film cooling effectiveness as the evaluation index. The flow characteristics and the cooling effectiveness distribution under different conditions are analyzed with numerical calculations. Results show that the film cooling effectiveness of the sister holes is 165%-412.5% of that of conventional cylindrical holes at a high blowing ratio, and the film cooling effectiveness of the sister holes with a 10° compound angle is higher than that of the sister holes with a -10° compound angle. Parameterized results reveal that the hole structure with a blowing ratio of 0.5, a compound angle of 10° and an inclination angle of 35° exhibits the best cooling performance.

Key words: sister holes, film cooling effectiveness, Taguchi method, blowing ratio, compound angle

中图分类号:

V231.1

王进, 孙杰, 赵占明, 张勃, 任晓栋, 谢公南. 基于结构参数分析的姊妹孔气膜冷却性能研究[J]. 航空学报, 2021, 42(7): 124775-124775.

WANG Jin, SUN Jie, ZHAO Zhanming, ZHANG Bo, REN Xiaodong, XIE Gongnan. Research on film cooling performance of sister hole based on structural parameter analysis[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 124775-124775.

参考文献

[1] 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.
[2] ACHARYA S. Film cooling simulation and control[J]. Heat Transfer Research, 2010, 41(6):601-626.
[3] 丁阳, 常海萍, 杜治能. 多排反向射流角气膜冷却特性研究[J]. 航空学报, 2013, 34(11):2472-2481. DING Y, CHANG H P, DU Z N. Investigation on characteristics of multiple rows of opposite lateral ejection angle film cooling[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(11):2472-2481(in Chinese).
[4] YANG C F, ZHANG J Z. Experimental investigation on film cooling characteristics from a row of holes with ridge-shaped tabs[J]. Experimental Thermal and Fluid Science, 2012, 37:113-120.
[5] ZHANG Y M, WEN Z X, PEI H Q, et al. Equivalent model of close-packed film cooling holes in nickel-based single crystal cooled blade based on crystallographic theory[J]. Chinese Journal of Aeronautics, 2019, 32(4):839-850.
[6] ZHANG S C, ZHANG J Z, TAN X M. Improvement on shaped-hole film cooling effectiveness by integrating upstream sand-dune-shaped ramps[J]. Chinese Journal of Aeronautics, 2021, 34(4):42-55.
[7] WU H, CHENG H C, LI Y L, et al. Effects of side hole position and blowing ratio on sister hole film cooling performance in a flat plate[J]. Applied Thermal Engineering, 2016, 93:718-730.
[8] HOU R, WEN F B, WANG S T, et al. Large eddy simulation of the trenched film cooling hole with different compound angles and coolant inflow orientation effects[J]. Applied Thermal Engineering, 2019, 163:114397.
[9] YAO J X, SU P F, HE J H, et al. Experimental and numerical investigations on double-jet film-cooling with different mainstream incidence angles[J]. Applied Thermal Engineering, 2020, 166:114737.
[10] FAWZY H, ZHENG Q, JIANG Y T, et al. Study of utilizing double lateral sub holes at different spanwise angles on blade film cooling effectiveness[J]. International Communications in Heat and Mass Transfer, 2020, 117:104728.
[11] ABDELMOHIMEN M A H, MOHIUDDIN A. Experimental investigation of film cooling from compound angle holes supplemented by secondary holes[J]. International Journal of Heat and Mass Transfer, 2019, 144:118678.
[12] ZHOU J F, WANG X J, LI J, et al. Effects of diameter ratio and inclination angle on flow and heat transfer characteristics of sister holes film cooling[J]. International Communications in Heat and Mass Transfer, 2020, 110:104426.
[13] TIAN K, WANG J, LIU C, et al. Effect of combined hole configuration on film cooling with and without mist injection[J]. Thermal Science, 2018, 22(5):1923-1931.
[14] CAO N, LI X, WU Z Y, et al. Effect of film hole geometry and blowing ratio on film cooling performance[J]. Applied Thermal Engineering, 2020, 165:114578.
[15] TIAN K, WANG J, LIU C, et al. Effect of blockage configuration on film cooling with and without mist injection[J]. Energy, 2018, 153:661-670.
[16] 赵占明, 翟郑佳, 刘超, 等. 分支孔结构对气膜冷却效率的影响研究[J]. 兵器装备工程学报, 2020, 41(2):216-220. ZHAO Z M, ZHAI Z J, LIU C, et al. Impact research of branch hole structure on film cooling effectiveness[J]. Journal of Ordnance Equipment Engineering, 2020, 41(2):216-220(in Chinese).
[17] SEO H J, KANG Y J, LEE H C, et al. Optimization of the configuration of the laidback fan-shaped film cooling hole with a lateral expansion angle of 10 degrees[J]. Applied Thermal Engineering, 2019, 153:379-389.
[18] HUANG Y, ZHANG J Z, WANG C H. Multi-objective optimization of round-to-slot film cooling holes on a flat surface[J]. Aerospace Science and Technology, 2020, 100:105737.
[19] ZAMIRI A, YOU S J, CHUNG J T. Large eddy simulation in the optimization of laidback fan-shaped hole geometry to enhance film-cooling performance[J]. International Journal of Heat and Mass Transfer, 2020, 158:120014.
[20] MADRANE A, AN H C, LENG J Z, et al. Shape optimization of inclined hole for enhanced film-cooling performance using discrete adjoint method[J]. International Journal of Thermal Sciences, 2020, 158:106542.
[21] TAGUCHI G, PHADKE M S. Quality engineering through design optimization[M]//Quality Control, Robust Design, and the Taguchi Method. Boston:Springer, 1989:77-96.
[22] WANG J, LIU C, ZHAO Z M, et al. Effect and optimization of backward hole parameters on film cooling performance by Taguchi method[J]. Energy Conversion and Management, 2020, 214:112809.
[23] SINHA A K, BOGARD D G, CRAWFORD M E. Film-cooling effectiveness downstream of a single row of holes with variable density ratio[J]. Journal of Turbomachinery, 1991, 113(3):442-449.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于结构参数分析的姊妹孔气膜冷却性能研究

Research on film cooling performance of sister hole based on structural parameter analysis

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 11

编辑推荐

Metrics

本文评价

[1]	李左飙, 温风波, 唐晓雷, 苏良俊, 王松涛. 基于深度学习的单排孔气膜冷却性能预测[J]. 航空学报, 2021, 42(4): 524331-524331.
[2]	于惠勇, 李华峰, 曾捷, 徐志伟, 黄继伟, 赵启迪. 可变弯度机翼后缘形态重构光纤监测技术[J]. 航空学报, 2020, 41(10): 223808-223808.
[3]	陈大为, 朱惠人, 李华太, 刘海涌, 周道恩. 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): 122651-122651.
[4]	张皓光, 谭锋, 安康, 楚武利, 吴艳辉. 缝式机匣处理及其轴向偏转角对跨声速轴流压气机稳定性的改善[J]. 航空学报, 2018, 39(8): 122101-122101.
[5]	刘双燕, 李玉龙, 薛璞, 石霄鹏. 裂纹参数和筋条布局对共振九宫板动态应力强度因子的影响[J]. 航空学报, 2018, 39(1): 221423-221423.
[6]	刘姝含, 朱战霞. 高超声速可变形双翼气动特性[J]. 航空学报, 2017, 38(9): 121352-121352.
[7]	邓雄, 夏智勋, 罗振兵, 李玉杰. 非对称出口合成双射流激励器矢量特性实验研究[J]. 航空学报, 2015, 36(2): 510-517.
[8]	丁阳, 常海萍. 涡轮叶片冷却有效性分析[J]. 航空学报, 2013, 34(1): 46-51.
[9]	游良平;陶毓伽;蔡军;梁世强;淮秀兰;顾维藻. 涡轮叶片前缘复合冷却实验[J]. 航空学报, 2009, 30(9): 1618-1623.
[10]	朱惠人;许都纯;刘松龄. 气膜孔形状对排孔下游冷却效率的影响[J]. 航空学报, 2002, 23(1): 75-78.
[11]	杨秋澄;亢清珍. 超音速旋转弹翼式“X-X”型导弹弹翼部分的诱导滚转力矩[J]. 航空学报, 1983, 4(1): 8-15.