涡轮平面叶栅变几何试验研究  

Variable Geometry Experimental Study of a Turbine Plane Cascade

作　　者：陈升[1] 邱超[1] 宋华芬[1] 

机构地区：[1]上海交通大学机械与动力工程学院,上海200240

出　　处：《热能动力工程》2011年第1期7-12,118,共6页Journal of Engineering for Thermal Energy and Power

摘　　要：通过建立变几何平面叶栅试验台,测量了平面叶栅在不同安装角下的叶片表面静压分布、出口总压分布和出口气流角。详细分析各种气动参数随叶片安装角的变化规律,并将试验测得的叶栅各种损失随转角的变化与3种损失模型的预测结果进行了比较,结果表明:在测量的转角范围内,随着安装角的增大,叶片表面扩压断明显增加,叶栅出口气流角也会随之增大,叶栅总损失不断减小。其中,叶型损失先减小后增大,端部二次流损失和叶顶间隙损失都是减小的。Through the setting-up of a variable geometry plane cascade test rig,measured were the blade surface static pressure distribution,outlet total pressure distribution and outlet gas flow angles of a plane cascade at different installation angles.Furthermore,the regularity governing the change of various aerodynamic parameters with blade installation angles was analyzed in detail.The change of various losses of the cascade with deflection angles,which were measured during the test,was compared with the results predicted by using three loss models.The research results show that in the range of the deflection angles being measured,the blade surface diffusion section will increase conspicuously with an increase of the installation angle and the outlet gas flow angle of the cascade will also increase.Moreover,the total loss of the cascade will constantly decrease.Among them,the blade profile loss will first decrease and then increase,and both the secondary flow loss at the two ends and blade tip clearance loss will invariably drop.

关 键 词：平面叶栅 变几何 安装角 损失 出口气流角 

分 类 号：TK474[动力工程及工程热物理—动力机械及工程]