直升机用轴流风机变工况性能研究  

Off-design Performance Study of Axial Flow Fan for Helicopter

作　　者：李明[1] 高红霞[1] 余建祖[1] 周懿[1] 

机构地区：[1]北京航空航天大学,北京100191

出　　处：《流体机械》2010年第10期7-12,共6页Fluid Machinery

摘　　要：针对某直升机滑油冷却用前置导叶型轴流风机,提出了一种变工况性能的理论计算方法,同时对损失计算模型进行了修正,在确定风机入口冲击损失系数时采用了理论分析结合数值计算和试验结果的方法。3种结果的比较显示风机的变工况性能理论计算方法的可靠性较高。结果表明,边界层厚度在小流量范围内较大,且都是从叶顶到叶根逐渐减小;直升机飞行高度增加会导致边界层分离、射流-尾迹区域宽度扩大等影响风机效率的不良因素,必须对风机进行变工况性能的优化设计。本文为直升机滑油冷却系统的高空工作性能预测提供了一种可行的方法。A theoretical calculation method for off-design performance is put forward for an axial flow fan with prerotator of oil cooling system in helicopters,including correction of the loss calculating model of the axial flow fan.And shock loss coefficient at fan inlet was calculated by the way of comparing the results of theoretical calculation,experiment and numerical calculation.The theoretical results for off-design performance show good agreement with experiment results and numerical results.The results show that boundary layer is thicker at low flow rate conditions,and decreases gradually from blade tip to hub area;and optimization design for off-design performance of the fan should be absolutely necessary because increment of helicopter flight altitude causing bad factors such as boundary layer separation,widening of jet-wake area.This paper supplies a reliable method for estimating the altitude performance of lubricating system of helicopter.

关 键 词：轴流风机 变工况性能 冲击损失系数 额定工况 边界层厚度 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]