二维扩压叶栅非定常涡面分析  

Analysis of unsteady vortex sheet in 2-D axial compressor

作　　者：周晓勃[1] 侯安平[1] 周盛[1] 

机构地区：[1]北京航空航天大学航空发动机气动热力重点实验室,北京100191

出　　处：《航空动力学报》2008年第8期1466-1473,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(10477002)

摘　　要：轴流压气机内流动是典型的非定常旋涡流动,而现有压气机分析设计体系在定常假设下以流场空间结构为对象.研究压气机内真实流动的途径之一是分析流场时空结构.把转/静叶片交错排列简化为单叶片排,再简化成2-D扩压叶栅.从叶栅非定常涡面的角度来描述非定常旋涡流场时空结构.作为举例,利用合成射流控制涡面演化,改善流场时空结构.此涡面简化模型可为进一步研究叶轮机叶排间干扰复杂流场的时空结构提供分析工具.The flowfield in turbomachinery is characterized by unsteady vortex flow. Contradictorily, the current analysis and design system of axial compressor is based on the spatial structure of the flowfield under the assumption of steady flow. It is understood that one of the methods to investigate the real flow inside the axial compressor is to analyze the temporal spatial structure of the flowfield. In this paper, an axial compressor stage embedding interlaced rotor and stator rows was simplified into a single blade row, and then further into a 2 D compressor cascade. In this way, the temporal spatial structure of the unsteady vortex flowfield could be described from the angle of unsteady vortex sheet of the cascade. For illustration, the temporal-spatial structure of the flowfield in cascade was transformed through controlling the evolution of vortex sheet by synthetic jet normal to the suction sur face of the cascade. The presented unsteady vortex sheet model could be used as an analysis tool for further research on the temporal spatial structure of stator/rotor interaction in multistage turbomachinery flowfield.

关 键 词：轴流压气机 非定常旋涡流动 涡面 流场时空结构 

分 类 号：V211.15[航空宇航科学与技术—航空宇航推进理论与工程]