高负荷压气机静叶根部叶型气动性能实验研究

Experimental Investigation on Performance of a Profile at Cascade Hub in a High Load Compressor Stator

关键词:  静叶  高负荷  平面叶栅  气动性能  实验研究

Key words:  Compressor stator  High load  Cascade  Aerodynamic performance  Experimental investigation

摘要:

为研究高负荷压气机静叶根部流动状态，抽取该静叶根部叶型并模化成为平面叶栅进行吹风实验，冲角变化范围为-6°～+6°、进口马赫数变化范围为0.5～0.7。对叶栅出口截面气动参数进行了详细的测量，结果表明:非正冲角时叶展中部节距平均总压损失系数小于等于0.036，尾迹宽度和总压损失峰值随马赫数变化均不明显，正冲角时尾迹宽度和总压损失峰值急剧增加；端壁处的压力梯度随马赫数和冲角的增加而增加；0°冲角下随马赫数的增大，出口叶展中部截面二次流动能系数增加，二次流动得到加强，高能量损失区域增大并且尾迹略有变宽。

Abstract:

In order to study the flow field at the hub zone in a high load compressor stator，profile of the stator hub had been extracted and modeled into a cascade. A detailed experimental investigation on the cascade with the incidence ranges from -6° to +6° and inlet Mach number ranges from 0.5 to 0.7 was carried out. The aerodynamic parameters at the outlet of the cascade were measured in detail. The results show that，at the incidence no greater than 0°，the pitch-averaged total pressure loss coefficient at mid-span is no greater than 0.036，neither the peak value of total pressure loss coefficient nor the width of wake changes significantly with the inlet Mach number. With the incidences greater than 0°，both the width of the wake and the peak value of total pressure loss will grow rapidly. Pressure gradient at the endwall increases with the increase of inlet Mach number and incidence. At 0° incidence，as the inlet Mach number grows，the secondary flow kinetic energy coefficient will grow and the secondary flow will be enhanced，and there is a slight increase in the area of high energy loss coefficient and the wake width，too.