带直肋及气膜出流的回转通道内冷气流动特性  

Experimental Study of Flow Characteristics in Two-Pass Channel with Ribs and Cell Film Cooling

作　　者：刘军亮[1] 徐国强[1] 丁水汀[1] 陶智[1] 邓宏武[1] 

机构地区：[1]北京航空航天大学航空发动机气动热力重点实验室,北京100083

出　　处：《航空动力学报》2005年第5期827-830,共4页Journal of Aerospace Power

摘　　要：将航空发动机高压涡轮叶片内冷通道进行简化,以实验方法研究了带90°直肋及气膜出流的变截面回转通道内冷气的流动特性。根据肋和气膜孔的结构特点,将通道划分为若干个特征单元。结果表明:与无气膜出流时相比,通道出口段存在气膜出流时其有效压力分布发生了较大的变化,使得整个出口通道的有效压力下降,在气膜孔附近压力下降更为明显。在其他条件不变时,与单元内其他位置的气膜孔相比肋后气膜孔出流量较大。Experiments have been carried out to study flow characteristics of film cooling outflow in two-pass channel. The two-pass channel of a real turbine blade was simplified. Film bleed hole are distributed along the outlet section surface. Experimental data have been analyzed by dividing the outlet section into several typical cells with rib and film cooling. Experimental results indicate that the effective pressure distribution of the outlet section changes significantly compared with no film cooling outflow and that the flow friction of the whole section decreases due to the influence of film bleeding. The outflow rate of the film bleed hole is the largest at the back of a rib.

关 键 词：航空、航天推进系统 回转通道 流动特性 肋 气膜冷却 

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]