摘要
在某直径6cm级的微型涡轮发动机MJ-S1研制中微型扩压器方案得到了改进,改进型微型扩压器由完整的主叶片和通道后部的分流叶片构成,可以避免气流的强烈掺混,降低转弯段内气流速度,减小流动损失.介绍了这种扩压器的设计方法,采用数值模拟的方法研究了设计参数通道面积和叶片角分布对扩压器性能的影响.MJ-S1最佳的改进型扩压器具有上凸的通道面积分布和接近线性的叶片角分布,该扩压器在压气机级中工作时总压恢复系数接近0.9.
The improved micro diffuser was suggested in the design of a 6cm-diameter micro turbine engine MJ-S1. The improved micro diffuser,which is composed of the full blades and splitters in the passage rear,can avoid significant mixing of airflow and air velocity of annular turning bend while reducing Mach number losses. The design method of the improved diffuser was put forward in this paper. The effects of passage area and blade angle on the diffuser characteristic were studied by using the computation fluid dynamic code NAPA. The diffuser has higher performance when the passage area distribution is convex and the blade angle is nearly linear. The calculation results show that the total pressure recovery coefficient of the improved diffuser can approach 0.9,when it is operated in the centrifugal compressor stage.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第5期1110-1116,共7页
Journal of Aerospace Power
关键词
改进型
微型扩压器
设计方法
数值模拟
总压恢复系数
improved
micro diffuser
design method
numerical simulation
total pressure recovery coefficient
