多孔层板冷却有效性的研究  

Experimental Investigation of Cooling Effectiveness of Laminate Porous Plates

作　　者：全栋梁[1] 刘松龄[1] 李江海[1] 许都纯[1] 游绍坤[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《航空动力学报》2004年第4期520-524,共5页Journal of Aerospace Power

基　　金：国防"973"资助项目(JC2000050500501);西北工业大学博士论文创新基金(CX200315)

摘　　要：在大尺寸低速回流风洞中对应用于涡轮叶片的2种绕流结构4块单双层多孔层板进行了流阻特性和冷却有效性的实验研究,结果表明多孔层板有很高的冷却有效性,流阻的大小和冷却有效性的高低主要取决于多孔层板的开孔率,开孔率越大,流阻越小,冷却有效性越高。本文所设计的层板结构参数和试验结果对层板在航空发动机涡轮叶片中的应用有参考价值。Four typical configurations of laminate plates for ultrahigh temperature turbine blade were made and tested in a large scale low speed close-looped wind tunnel. The internal flow resistance and the cooling effectiveness were obtained. The experimental results show that the very high cooling effectiveness can be achieved by using laminate plates and the ratio of the hole area to the plate area plays the most important role in determination of the cooling effectiveness and the internal flow resistance, the higher the ratio, the smaller the resistance and the higher cooling effectiveness. The research results are of reference value for the application of the laminate plates to aeroengine turbine blade.

关 键 词：航空、航天推进系统 涡轮叶片 多孔层板 流阻特性 冷却有效性 

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]