亚音叶型前缘形状对附面层参数影响
Effects of Leading-Edge Geometry on Boundary Layer Parameters in Subsonic Airfoil
于贤君 1朱宏伟 1刘宝杰1
作者信息
- 1. 航空发动机气动热力重点实验室,先进航空发动机协同创新中心,北京航空航天大学能源与动力工程学院,北京100191
- 折叠
摘要
采用数值模拟方法研究了圆弧形、椭圆形和曲率连续无吸力峰前缘对叶型附面层发展的影响规律.通过提取不同工况下叶面附面层参数并结合叶表附面层速度型的变化,发现前缘吸力峰对叶型性能的影响本质在于吸力峰影响了附面层的起始发展状态.前缘吸力峰扩压参数Dspike过强会导致附面层起始发展状态恶化,造成提前转捩,甚至出现分离泡,叶表附面层迅速增厚,叶型损失增大,可用攻角范围减小.研究还表明,所设计的曲率连续无吸力峰前缘在任意工况总可以消除吸力面或压力面近前缘的吸力峰,从而使得叶表附面层的起始状态优于其它前缘叶型,因此气动性能要更好.
Abstract
The effect of circular,elliptical and curvature continuous leading edge on the development of boundary layer is studied by numerical simulation method.It is found that the influence of the leading edge suction peak on the aerodynamic performance in subsonic compressor blade is due to the fact the suction affects the initial development state of the boundary layer by extracting the parameters of the boundary layer under different working conditions and the velocity pattern of the bounder layer.The leading edge of the suction peak diffusion parameter Dspike is too strong will lead to the initial state of deterioration of the boundary layer,resulting in early transition,or even separation bubble,blade surface layer of rapid thickening,loss of blade increases,the available attack angle range reduced.The study also shows that the design of curvature continuous spikeless leading edge in any condition can always eliminate the suction surface or pressure surface near the leading edge of the suction peak,so that the initial state of the blade surface layer is better than the other leading edge,so aerodynamic performance should be better.
关键词
叶型前缘/亚音叶型/附面层/数值分析/压气机Key words
leading edge/subsonic compressor blade/boundary layer/numerical analysis/compressor引用本文复制引用
基金项目
国家自然科学基金资助项目(51476004)
国家自然科学基金资助项目(51376014)
出版年
2017
NETL
NSTL
维普
万方数据