叶型任意位置损失提取方法及其应用

Method for Extracting the Boundary Layer Loss in Any Position of the Cascade and Its Application

通过理论推导将边界层总压损失与附面层能量损失厚度、主流速度及密度等参数相关联,用于计算叶型任意位置边界层流动损失大小,并使用数值模拟软件MISES以及CFX完整地校验了该损失分析方法的可靠性,利用该损失提取方法处理了MISES及CFX计算结果,分析了一个典型跨声速叶型吸力面和压力面边界层损失在叶栅内部的发展过程及其随进口气流角的变化规律,从而揭示了该跨音叶型边界层损失的主要来源,为叶型优化设计提供了基础理论支持。

Total pressure loss coefficient is related to the boundary-layer energy thickness, boundary- layer edge velocity and density by theoretical derivation which can be used to calculate the boundary layer flow loss in any position of the cascade. The reliability of the formula is examined by processing the calculation results of MISES and CFX. Then the loss formula is used to analyse the development of the suction and pressure surface boundary layer loss caused by viscosity and the its variation with the inlet flow angle in a typical transonic compressor cascade. The analysis results reveal the main source of the boundary layer loss in the transonic cascade which provide the basic theory support for the optimization of the airfoil shape.