进气畸变与旋转失速诱导叶片振动的相关性分析  

Correlation analysis of blade vibration induced by inlet distortion and rotating stall

作　　者：杜建建[1] 李舜酩[1] 方立成[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2011年第11期2623-2629,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(50675099)

摘　　要：为了定量地分析进气畸变与旋转失速两种气动载荷之间以及两者单独激励下叶片位移响应之间的相关程度,基于双级低速轴流压气机试验器上进行的进气畸变试验与旋转失速试验所得的流场数据,对叶片在两者单独激励下的振动特性进行仿真计算,并从统计学的角度对变量之间的相关性进行分析.结果表明:两种流场压力数据之间相关性极高,说明两者共享的特征较多;节点位移响应之间的相关程度低于两种压力载荷之间的相关程度;同一叶型截面上节点位移响应之间的相关系数曲线大致成不对称的V字型;沿叶身截面从叶根至叶尖节点位移响应之间的相关系数逐渐降低,主要与边界条件有关.To analyze correlation degree between inlet distortion and rotating stall quantitatively,as well as blade displacement responses induced by them,blade vibration characteristics were simulated under inlet distortion or rotating stall by software ANSYS based on measurement data obtained from two stage low speed axial compressor,and correlation analysis between variables was made with statistics theories.The results indicate：two flow pressure data are highly related,and many characteristics are shared by them.Correlation degree between displacement responses is lower than that between inlet distortion and rotating stall.Correlation coefficient curve between displacement responses of the same section is of roughly asymmetrical V shape.Correlation coefficient between displacement responses of blade body from root to tip decreases gradually as it is mainly related to boundary conditions.

关 键 词：相关分析 叶片振动 进气畸变 旋转失速 数值仿真 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]