论文部分内容阅读
针对NASA的Rotor 67进行数值模拟以揭示轮毂角区边界层分离诱发机制和进一步完善角区分离控制方法。数值结果表明,角区边界层在强逆压梯度和叶片后半段较大曲率变化的双重影响下引发了分离。通过对比分析不同抽吸方案对角区流动的影响发现,在轮毂90%弦长位置处采用边界层抽吸,且相对抽吸流量为0.14%时,可完全消除轮毂角区内的回流流体和脱落涡结构,抽吸效果最佳。在保证转子压比基本不变的情况下,最大可使得转子效率提高0.29%,落后角减小4°。轮毂抽吸还抑制了叶根附近低能流体堆积效应,有助于改善叶片载荷分布和出口气流参数的分布。
The Rotor 67 for NASA was numerically simulated to reveal the mechanism of the separation of the boundary layer in the corner of the hub and to further refine the separation control method. The numerical results show that the boundary layer in the corner zone induces separation under the dual influence of the strong pressure gradient and the larger curvature of the second half of the blade. By comparing and analyzing the influence of different pumping schemes on the flow in the corner zone, it is found that when the boundary layer suction is adopted at the 90% chord length of the hub and the relative suction flow rate is 0.14%, the reflux fluid in the hub corner zone can be completely eliminated Off vortex structure, the best suction. Under the condition of keeping the pressure ratio of the rotor basically unchanged, the maximum rotor efficiency can be increased by 0.29%, and the backward angle can be reduced by 4 °. Hub suction also suppresses the accumulation of low-energy fluid near the root and helps to improve the blade load distribution and outlet airflow parameters distribution.