高性能亚音速平面叶栅风洞设计  

Design of high-specificatrion sub-sonic cascade tunnel

作　　者：张宏[1] 李光里[1] 赵长宇[1] 

机构地区：[1]沈阳航空航天大学飞行器动力与能源学院,辽宁沈阳110136

出　　处：《沈阳航空工业学院学报》2010年第5期18-22,共5页Journal of Shenyang Institute of Aeronautical Engineering

摘　　要：论述了用于测量压气机和涡轮叶片在亚声速状态下的二维气动特性的平面叶栅风洞设计问题。风洞采取暂冲式直流型式,由压缩机和储气罐提供高压气流,稳定段前采用大开角扩散段,并在扩散段进口段设置整流锥,锥后加装两层球面整流网,收缩段与稳定段连接处加设唇口,唇口与收缩段型面曲线均为双三次曲线,为防止试验段由于内外压力差导致漏气所造成的压力损失,在试验段外部加装了驻室结构,出口气流通过消声塔降低噪音再排入大气。风洞整体参数居于国内领先水平。Some design questions of a cascade tunnel to measure planar aerodynamic parameters of compressor and turbine cascades by sub-sonic speed.is discussed.The tunnel is intermittent blowdown wind tunnel,the high pressure airflow is supplied by air compressor and air container,settling chamber and airflow pipeline are linked by diffuser,and there is a cone to commutate airflow and two gauze screens set in the diffuser,the contraction cone and settling chamber joined by a lip,the curve of lip and contraction is double-cube curve.There is a plenum chamber out of the test section,which could avoid air leaking as a result of differential pressure,the function of anechoic chamber is to reduce noise.

关 键 词：叶栅风洞 压气机叶片 涡轮叶片 驻室 大开角扩散段 噪声 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]