双向进气时扰流柱通道内流动与换热特性试验研究  

Experimental Research on Flow and Heat Transfer Characteristic in Pin Fin Passage with Double-Inlet

作　　者：任芳[1] 潘炳华[1] 郭文[1] 朱惠人[2] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500 [2]西北工业大学,陕西西安710072

出　　处：《燃气涡轮试验与研究》2013年第1期26-29,共4页Gas Turbine Experiment and Research

摘　　要：试验研究了两端进气时涡轮叶片尾缘扰流柱通道内的流动与换热特性。试验模型对涡轮叶片尾缘横肋、扰流柱通道进行了简化,并放大四倍,保留了叶片尾缘的基本特征。试验中通过调节扰流柱通道和横肋通道的流量分配,得到各测点的压力分布和努赛尔数据分布。研究结果表明,扰流柱通道两端进气结构,使整个通道的压力分布和换热分布比较均匀,克服了一端进气时流阻和压力损失较大引起的叶尖换热较差的缺点。The tests were carried out to study the heat transfer characteristic of the pin fin at the turbine blade trailing edge in the double-inlet case. The test model of turbine blade trailing edge rib and pin fin were simplified and magnified four times so to keep the basic characteristics of trailing edge. Pressure distri- bution and Nusselt number distribution at measuring points were obtained through regulating flow between pin fin passage and rib passage. The results showed that, with double-inlet structure, the distribution of pressure and heat transfer were relatively uniform , and the problem of poor heat transfer in blade tip caused by large resistance of flow and much pressure loss in pin fin passage with one inlet was conquered.

关 键 词：航空发动机 涡轮 双向进气 扰流柱 换热特性 流量分配 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]