高负荷压气机叶栅附面层吹吸对气动性能影响研究

Research of the Aerodynamic Performance Effect of Boundary Layer Blow or Suction in High Load Compressor Cascade

为研究压气机叶栅吹吸气体对附面层分离控制和气动性能的影响,利用数值计算的方法对叶栅流场进行模拟。首先研究吸气量对叶栅气动性能的影响规律,研究结果表明,当吸气孔的位置在距离叶片前缘60%的轴向弦长处时,存在一个最佳吸气量,当吸气量等于进气量的0.8%时,叶栅吸气对附面层分离的抑制效果最佳,对压比的提升最明显。提出四种叶栅开孔吹吸气方案,即吸附式叶栅、吸吹式叶栅、吹吸式叶栅和双吸式叶栅,通过流场和气动性能的对比,发现双吸式叶栅对附面层分离的抑制效果和对气动性的改善效果均最为显著。

To research the separation flow control and the aerodynamic performance effect of boundary layer blowor suction,the cascade flow fields are simulated numerically. Firstly,the effect of suction mass-flow on the aerodynamic performance is researched. The results show that there is a optimal suction mass-flow when the suctionholes are located at 60 percent blade chord away from the leading edge. When the suction mass-flow is 0.8 percent of the air inflow,the effect of the separation flow control and increasing pressure ratio are the best. The fourkinds of hole scheme are carried out,respectively the aspirated cascade,the aspirated then blown cascade,theblown then aspirated cascade and the aspirated then aspirated cascade. Contrasting with the separation flow controland the aerodynamic performance effect,the effect of the aspirated then aspirated cascade is the best.