小尺寸多级轴流压气机喘振现象试验  

Experiment on surge phenomenon of small multi-stage axial compressor

作　　者：贺象[1,2,3] 马宏伟[2,3] 银越千[1] 单晓明[1] 姚峥嵘[1] 

机构地区：[1]中国航空工业集团公司中国航空动力机械研究所,湖南株洲412002 [2]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191 [3]先进航空发动机协同创新中心,北京100191

出　　处：《航空动力学报》2016年第8期1957-1963,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(51161130525);航空发动机气动热力国家级重点实验室基金(91400410205130C41007)

摘　　要：针对某小尺寸多级轴流压气机,在首级转子叶顶沿弦向布置Kulite动态压力传感器以及在后面级插入高频压力探针,通过动态测量试验,研究不同转速下多级轴流压气机喘振现象.结果表明:在中高转速下,该压气机深度喘振是由模态波扰动发展成旋转失速,从而引起流动堵塞,最终导致流动崩溃所造成的;在低转速下,压气机轻度的经典喘振由模态波直接引起的,在喘振周期内一直伴随有旋转失速的产生、发展和消失.An experimental investigation on the compressor surge phenomenon was carried out in a small multi-stage axial compressor under different rotor speeds. The dynamic pressure signals of 1st rotor tip were measured by the Kulite dynamic pressure transducers and the fast response pressure probes. Results indicated that, at mid and higher rotor speed, the modal wave appears and evolves into rotating stall in the pre-surge period and, subsequently, the compressor is rapidly brought to deep surge by the huge blockage of the stall cell; However, at lower rotor speed, the classical surge is directly triggered by modal wave with the existence of rotating stall in the surge cycle.

关 键 词：多级轴流压气机 动态压力测量 旋转失速 压气机喘振 模态波 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]