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。
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.
作者
王进
孙杰
赵占明
张勃
任晓栋
谢公南
WANG Jin;SUN Jie;ZHAO Zhanming;ZHANG Bo;REN Xiaodong;XIE Gongnan(School of Energy and Environmental Engineering,Hebei University of Technology,Tianjin 300401,China;Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,Tsinghua University,Beijing 100084,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China;School of Marine Science and Technology,Northwestern Polytechnical University,Xi'an 710072.China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2021年第7期325-335,共11页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(51806118,51806057)。
关键词
姊妹孔
气膜冷却效率
田口方法
吹风比
偏转角
sister holes
film cooling effectiveness
Taguchi method
blowing ratio
compound angle
