某大涵道比风扇轮毂型线数值计算  

Numerical Calculation of Hub-shape Contouring on a High Bypass Ratio Engine Fan

作　　者：刘晓锋 刘世文 杨小贺 陈云永 LIU Xiao-feng;LIU Shi-wen;YANG Xiao-he;CHEN Yun-yong(AECC Commercial Aircraft Engine CO.,Ltd.,Shanghai 201108,China)

机构地区：[1]中国航发商用航空发动机有限责任公司,上海201108

出　　处：《航空发动机》2018年第4期26-33,共8页Aeroengine

基　　金：航空动力基础研究项目资助

摘　　要：为了改善风扇叶根的二次流动,基于某原型方案,采用数值模拟方法研究了轮毂型线对大涵道比民用发动机风扇流场的影响。研究结果表明:凹形轮毂型线对风扇根部流动的影响主要体现在从下凹位置开始的加速流动作用。靠近风扇尾缘是较优的轮毂下凹最深位置,对根部流动存在2种改善作用,即流路收缩带来的加速流动作用,在提高风扇根部出口子午速度的同时,提高了10%叶高附近吸力面表面流体速度,抑制该叶高靠近尾缘处流体回流;由于轮毂下凹最深位置靠近尾缘,轮毂型线在靠近风扇出口时可以维持在凹曲线形式,减弱风扇角区吸力面表面回流。轮毂下凹深度对风扇内涵的压比和效率呈现单调影响。改进后的轮毂型线计算结果与原型方案相比,风扇吸力面极限流线改善,全流量范围内风扇内涵效率提升。In order to improve the secondary flow of fan blade root,the effect of hub-shape contouring on the flow field of a high bypass ratio civil engine fan was studied by using numerical simulation method based on the prototype plan.The results show that the effect of concave hub-shape contouring on the flow of fan blade root is mainly reflected in accelerating flow,starting from the concave position.The most deep concave position of hub is near to the fan trailing edge,which has improvement effect in two aspects,the accelerating flow,caused by the flow path contraction,enhances both the meridian velocity at fan root exit and the suction-surface flow velocity near to the 10%of blade height location,and therefore restrains the fluid recirculation near to the trailing edge of the blade height.Since the most deep concave position of hub is near to the fan trailing edge,the hub-shape contouring remains concaved near to the fan exit,and the suctionsurface recirculation in fan angular region is reduced.The depth of hub concave influences the pressure ratio and efficiency of the fan core monotonously.Compared with the prototype plan,the suction surface limiting stream line of fan is improved,and the core efficiency of fan in full flow range is enhanced.

关 键 词：大涵道比风扇 轮毂 型线 数值模拟 民用发动机 

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]