端弯联合弯叶片对叶栅旋涡结构和气动性能的影响

Effects of End-Bowed Blade and Dihedral Blade Technology on Vortex Structure and Aerodynamic Performance in a Compressor Cascade

为了研究弯叶片弯角、端弯弯高和端弯弯角三个参数对扩压叶栅流道内的旋涡结构和气动性能所造成的影响大小和交互作用的主次顺序,以环形扩压叶栅为研究对象,通过正交试验设计的方法,对试验结果进行分析。结果表明,存在一个最佳弯叶片弯角以平衡集中脱落涡和壁角涡对叶栅出口总压损失分布的影响;弯叶片弯角的提高会导致壁角涡减弱并且涡核靠向端壁,集中脱落涡增强并且涡核靠向流道中部;旋涡结构的变化进而导致端部高损失区域损失减小并且靠向集中脱落涡涡核,流道中部损失增厚并且向中部收缩。端弯的弯高和弯角对角区的影响明显强于流道中部;壁角涡强度的提高导致端部损失的增加;集中脱落涡涡核向端壁移动,导致流道中部损失向端区扩散,但损失减小有限。

In order to study the effects and interaction of the dihedral angle,end-bowed height and angle on vortex structure and aerodynamic performance,the result in an annular compressor cascade were analyzed through orthogonal experimental design. The results show the existence of best dihedral angle to balance the effect on exit total pressure loss distribution of concentrated shedding vortex and corner vortex. The improvement of dihedral angle leads to the weakening of concentrated shedding vortex and the vortex core towards the end wall,while concentrated shedding vortex is enhanced and the core of it is close to the middle span. The change of vortex structure makes the loss decrease in the high loss region and the region gets close to the core of concentrated shedding vortex,while the loss of middle span gets thickening and shrinks to the center. The influence of endbowed height and angle is more significant on the end region than on the middle span. The improvement of corner vortex strength makes the loss of end region increase,while the movement of concentrated shedding vortex＇s core leads to the proliferation of loss to the end region from the middle,but the decrease of loss is limited.