摘要
采用流线曲率法、端部势流场分析加附面层修正等数值模拟手段 ,就分流机匣对风扇 /压气机性能的影响展开研究 ,主要针对分流机匣端部中弧线形状、端弧形状 ,以及其轴向位置所引起的风扇 /压气机特性变化规律进行了分析。研究结果表明 :分流机匣几何参数及其轴向位置对整个风扇 /压气机的性能有相当大的影响 ,对其几何参数的合理选取可以使风扇 /压气机在较大的涵道分流比范围内 ,有效控制机匣内外表面附面层流动状况 ,在抑制紊流附面层分离 ,改善堵塞裕度方面有独特作用。
A numerical method was applied to a S2,stream-surface streamline curvature approach to calculate the fan/compressor performance.The flow field around the splitter lip was found by calculating the potential flow field along the splitter surface and subsequent turbulent boundary layer analysis.The potential flow field was found by using a singularity method.A fan/compressor component was selected as an example to investigate the splitter lip effects on performance of fan/compressor system.A number of different splitter lip geometric parameters,such as the axial location,shape of splitter lip meanline and nose was considered and their effects on the fan/compressor performance were discussed.A proper selection of geometric parameters will be a great help to controll effectively the boundary layer flow on splitter lip surface.As a result,the boundary layer separation can be delayed and the choking can be improved.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2001年第1期33-37,共5页
Journal of Aerospace Power
