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.
出处
《流体机械》
CSCD
北大核心
2010年第10期7-12,共6页
Fluid Machinery
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
axial flow fan
off-design performance
shock loss coefficient
rated condition
boundary layer thickness
