叶片开槽对大涵道比风扇的流动控制研究  

Analysis on Flow Control of High Bypass Ratio Fan by Blade Slot

作　　者：刘恩波 周正贵[1] LIU Enbo;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》2023年第3期168-171,共4页Machine Building & Automation

基　　金：国家科技重大专项(2017-Ⅱ-0001-0013)。

摘　　要：提出利用空心结构在涡扇发动机大涵道比风扇内部从前缘到吸力面开槽,利用来流速度冲量在吸力面形成微喷气控制吸力面附面层的流动控制方法。研究不同槽道进、出口宽度和出口位置对二维叶栅的影响,选取最优方案进行三维叶片开槽。结果表明:叶片开槽可有效抑制吸力面附面层发展,减少附面层和尾迹损失,使效率增加了0.46%,失速裕度增加了1.8%,总压比增加了1.3%;微喷气流量适中并作用在吸力面附面层发展的起始位置时对附面层的抑制效果最好。A flow control method is proposed to control the layer on the suction surface by using the micro-jet formed on the suction surface with the inflow velocity impulse and the hollow structure slotted from the leading edge to the suction surface inside the fan blade of a high bypass ratio turbofan engine.The influence of different inlet and outlet widths and outlet positions of slot channels on the two-dimensional slotted cascades was studied,and the three-dimensional blade was slotted with the optimal scheme.The results show that the blade slot can effectively restrain the development of the layer on suction surface after the shock wave,reduce the losses of boundary layer and wake,and increase the efficiency by 0.46%and stall margin by 1.8%,and the total pressure ratio grows by 1.3%.When the jet flow is moderate and acts on the initial position of the development of the layer on suction surface,the inhibition effect on the layer is the best.

关 键 词：涡扇发动机 大涵道比风扇 开槽叶片 流动控制 附面层分离 数值模拟 

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]