摘要
针对某型跨声轴流风扇大小叶片转子,通过优化去除小叶片中弧线形状的影响,对比分析了最高效率点工况下小叶片弦长对转子气动性能的影响.发现小叶片前缘膨胀波可以调整大叶片壁面附面层逆压力梯度段的长度和逆压梯度的强度.正确选择小叶片前缘位置可以降低附面层损失,抑制大叶片后部分离,合理分配气动负荷.
An axial transonic fan with splitter was designed. An optimization method was used to eliminate the influence of the splitter camber shape. The effect of splitter chord length on the aerodynamic performance of the fan rotor was analyzed under the maximum efficiency condition. The results show that the leading edge expanding wave can adjust the length of the main blade boundary layer negative gradient and its strength. Correctly selecting the splitter leading edge position can reduce the boundary loss, control the separation at the rear part of the main blade and produce optimal aerodynamic load distribution.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第12期2050-2054,共5页
Journal of Aerospace Power
基金
国家863基金(863-2-1-3-1)
关键词
航空
航天推进系统
轴流跨声风扇
大小叶片
弦长
激波
aerospace propulsion system
axial transonic fan
splitter
chord length
shock wave
作者简介
孙玺淼（1977-），男，天津人，博士生，主要从事叶轮机械风扇、压气机气动设计的研究．
