| 基于结构参数分析的姊妹孔气膜冷却性能研究 |
| |
| 引用本文： | 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. |
| |
| 作者姓名： | 王进 孙杰 赵占明 张勃 任晓栋 谢公南 |
| |
| 作者单位： | 河北工业大学能源与环境工程学院,天津 300401;清华大学热科学与动力工程教育部重点实验室,北京 100084;先进航空发动机协同创新中心,北京100191;西北工业大学航海学院,西安 710072 |
| |
| 基金项目： | 国家自然科学基金（51806118，51806057） |
| |
| 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 |
| 收稿时间： | 2020-09-22 |
| 修稿时间： | 2020-10-15 |
Research on film cooling performance of sister hole based on structural parameter analysis |
| |
| 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 Aeronautica et Astronautica Sinica,2021,42(7):124775-124775. |
| |
| Authors: | WANG Jin SUN Jie ZHAO Zhanming ZHANG Bo REN Xiaodong XIE Gongnan |
| |
| Institution: | 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 |
| |
| 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. |
| |
| Keywords: | sister holes film cooling effectiveness Taguchi method blowing ratio compound angle |
| 本文献已被 万方数据 等数据库收录！ |
| 点击此处可从《航空学报》浏览原始摘要信息 |
| 点击此处可从《航空学报》下载免费的PDF全文 |
|
