高负荷局部进气涡轮内部流场不均匀性数值研究  

Numerical Investigation of the Non-uniform Flow Field for a High Loaded Partial Admission Turbine

作　　者：陈帝云 钟兢军[1] 韩吉昂[1] 

机构地区：[1]大连海事大学轮机工程学院,大连116026

出　　处：《工程热物理学报》2016年第12期2549-2556,共8页Journal of Engineering Thermophysics

基　　金：辽宁省高等学校创新团队资助项目(No.LT2015004)

摘　　要：以高负荷局部进气涡轮为研究对象,对其进行了数值研究,并着重对该局部进气涡轮内部流场不均匀性进行了分析。结果表明:局部进气涡轮内部流场的流动情况十分复杂,局部进气堵塞段的存在,使其后面对应的动叶栅进出口速度矢量偏向周向,导致该区域叶片流道内形成了大尺度的旋涡结构,降低了流道的通流能力,增大了该区域的损失水平;各级动叶进出口静压沿周向分布极不均匀,从第一级动叶入口至第二级动叶出口,静压周向不均匀性参数分别为:1.5593、1.0179、0.9163和0.1551,不均匀性沿轴向逐渐衰减;处于不同周向位置的叶片表面压力分布差异明显,直接影响了动叶的做功能力。A high loaded partial admission turbine was taken as the research object,the numerical investigation was carried out and the non-uniform inner flow field of the partial admission turbine was analyzed in detail.Conclusions show that the inner flow field of partial admission turbine is rather complex,the velocity vectors at the inlet and outlet of the blade passages behind the blocking arc are driven to the circumferential direction which make the blade passages in these area exist large-scale vortex which lower the mass flow rate and efficiency of these passages.The static pressure profile on rotor/stator interface is circumferential non-uniform.Prom first stage stator outlet to second stage rotor outlet,the static pressure non-uniform parameters are 1.5593,1.0179,0.9163 and 0.1551.So the circumferential non-uniformity will decay along the axial direction.The pressure profiles are quite different to the blades at different circumference positions,which makes the power output of these rotor differ greatly.

关 键 词：高负荷 局部进气 涡轮 流场不均匀性 数值研究 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]