载荷分布规律对开槽压气机叶型气动性能的影响  

Influence of Load Distribution on Aerodynamic Performance of Slotted Compressor Blade

作　　者：曾凌霄 周正贵[1] ZENG Lingxiao;ZHOU Zhenggui(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2024年第2期20-24,共5页Machine Building & Automation

基　　金：国家科技重大专项项目(2017-Ⅱ-0001-0013)。

摘　　要：航空压气机叶片通道内流动呈强逆压梯度,为了减小流动损失、扩大稳定工作范围,针对压气机静子叶型提出一种新型开槽叶片,槽道由叶片前缘进气吸力面出气,使用来流速度冲量有效抑制吸力面附面层的发展。采用计算机数值模拟方法,研究不同吸力面峰值等熵马赫数位置的可控扩散叶型开槽对叶栅气动性能的影响。研究结果表明:在设计工况下,开槽可有效抑制吸力面附面层发展,降低叶栅损失,增加气流转角;吸力面峰值等熵马赫数位置越向尾缘,在整个进气角范围内,开槽降低损失程度越大,并且由于攻角越大吸力面附面层越厚,开槽降低损失程度越大。As the flow in aviation compressor blade channel assumes a strong reverse pressure gradient,this paper proposes a new type of slotted blade for the compressor stator blade in order to reduce the flow loss and expand the stable working range.Through the channel,the pressure inlets from the leading edge of the blade and exhales from the suction surface,and the inflow velocity impulse is used to effectively suppress the development of the suction surface and the boundary layer.The influence of controlled diffusion blade slot with different suction surface peak isentropic Mach number positions on the aerodynamic performance of cascade is studied by computer numerical simulation.The results show that under the design condition,slotting can effectively suppress the development of the suction surface boundary layer,reduce the cascade loss and increase the flow angle.The more the position of peak isentropic Mach number of the suction surface is toward the trailing edge,the greater the degree of loss reduction by slotting is in the whole range of inlet angle;the larger the angle of attack is,the thicker the boundary layer on the suction surface is,and the greater the reduction loss of slotting is.

关 键 词：压气机 叶栅 载荷分布 开槽叶型 气动性能 流动控制 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]