有错排射流冲击的受限长通道及出流孔流场的实验研究  

Flow field measurements in a confined channel and outlet hole with staggered jet array impingement

作　　者：刘海涌[1] 孔满昭[1] 刘松龄[1] 沈天荣[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：《推进技术》2006年第4期307-311,共5页Journal of Propulsion Technology

摘　　要：用五孔针对简化后的涡轮叶片错排射流冲击受限长通道及出流孔流场进行了详细的测量,着重研究受限通道及出流孔内的流动特性,获得通道和射流孔侧壁静压的变化规律。实验结果表明:受限通道内因射流诱导及壁面限制形成漩涡,使高速气流向通道侧壁甚至孔板面集中;出流孔内存在很强的逆时针方向漩涡,气流分离严重,流量系数仅为0.3;通道及射流孔压力沿流向呈加速下降趋势,通道侧壁压力在出流孔位置略有回升。Experimental results were presented to describe the flow behavor in low aspect ratio confined channel and outlet hole. Flow impinges target wall from twelve staggered jet holes and pours out with a sharp turning from a bigger outlet hole. Measurements were performed using a five-hole probe, Important results of the research include： Jet-induced swirl flow were found in the channel, which tended to push high velocity flow moving toward side walls or even to the top wall. A strong counter-clockwise vortex was observed in the outlet hole which led to serious flow separation and low discharge coefficient of around 0.3. Static pressure in channel and jet holes droped more rapidly in the downstream region, and channel pressure has shown a little recovery near the outlet hole.

关 键 词：射流 受限通道^+ 冷却 流动特性 流量系数 

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]