吹风比对楔形通道内异型气膜孔冷却效率的影响研究  

Research on the effect of blowing ratio on the cooling efficiency of shaped air film holes in wedge-shaped channels

作　　者：马立程 吴丽玲 郭春海[1,2] 杨卫华 张文武[1,2] Ma Licheng;Wu Liling;Guo Chunhai;Yang Weihua;Zhang Wenwu(Ningbo Institute of Materials Technology and Engineering,Ningbo 315201,China;Chinese Academy of Sciences Zhejiang Key Laboratory of Aero Engine Extreme Manufacturing Technology,Ningbo 315201,China;University of Chinese Academy of Sciences,Beijing 101408,China;College of Energy and Power Engineering,Nanjng University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]中国科学院宁波材料技术与工程研究所,宁波315201 [2]浙江省航空发动机极端制造技术研究重点实验室,宁波315201 [3]中国科学院大学,北京101408 [4]南京航空航天大学能源与动力学院,南京210016

出　　处：《空天技术》2024年第6期45-57,74,共14页Aerospace Technology

基　　金：宁波市自然科学基金(2023J413);宁波市“甬江引才工程”项目(2022A-210-G)。

摘　　要：针对楔形通道内一种适用于高吹风比工况的异型气膜孔的绝热冷却效率进行了研究,采用实验与仿真相结合的方法,对比分析了不同吹风比下该异型孔与传统圆柱型孔在展向的平均气膜冷却效率。研究结果表明:实验过程中,随着吹风比的减小,实验件壁面整体温度逐渐降低,绝热冷效逐渐升高,吹风比为2.5时,冷却效率最高;另外,通过实验分析了6组吹风比下的两种孔型的冷却效率,得到吹风比为5时,与圆柱型孔相比,异型孔的冷却效率提升最高;在数值仿真研究中,对异型孔实验件流体域进行绝热仿真,与同等工况下实验结果对比发现,两者吻合较好,平均相关系数大于0.97,平均相对误差小于1.8%。The adiabatic cooling eficiency of a shaped air film hole in a wedge channel for high blowing ratio conditions is investigated,and the average air film cooling efficiency of the shaped hole and the conventional cylindrical hole in the spreading direction under different blowing ratios is compared and analyzed by using a combination of experiments and simulations.The results show that:During the experiment,with the decrease of the blowing ratio,the overall temperature of the experimental part wall gradually decreases and the adiabatic cooling efficiency gradually increases,and the cooling efficiency is highest when the blowing ratio is 2.5.In addition,the cooling efficiency of the two hole types under six groups of blowing ratios is analyzed experimentally,and the highest cooling efficiency improvement is obtained when the blowing ratio is 5.In the numerical simulation study,the adiabatic simulation of the fluid domain of the experimental parts with shaped holes is carried out,and the comparison with the experimental results under the same working conditions reveals that the two are in good agreement,with an average correlation coefficient of more than 0.97 and an average relative error of less than 1.8%.

关 键 词：气膜冷却 异型孔 吹风比 冷却效率 绝热实验 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]