摘要
用任定准正交面方法对一个航空涡轮冷却器的离心压气机叶轮流场进行了三元计算，计算考虑了上下游边界条件的影响。用计算结果分析了叶轮流场品质，提出了改型措施并对改型叶轮流场进行了分析。
The three-dimensional flow field of a centrifugal impeller for aircraft cooling turbine is computed with quasi-orthogonal surface method in cluding the influence of upstream and downstream conditions.The calculated flow field of the centrifugal impeller and the improvement of the blade shape are discussed.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1995年第1期42-46,共5页
Acta Aeronautica et Astronautica Sinica
关键词
离心压气机
三维流动
叶轮
航空发动机
centrifugal compressors,three dimensional flow,impellers
