The effect of Reynolds number on transonic compressor blade rotor section

被引：5
|
作者：
Amiri, H. Beheshti [1 ]
Farahani, A. Shahrabi [1 ]
Khazaei, H. [1 ]
机构：
[1] Amirkabir Univ Technol, Dept Mech Engn, Tehran Polytech, Tehran, Iran
来源：
HEAT AND MASS TRANSFER | 2016年 / 52卷 / 10期
关键词：
Reynolds Number; Mach Number; Deviation Angle; Loss Coefficient; Choke Flow;
D O I：
10.1007/s00231-015-1715-z
中图分类号：
O414.1 [热力学];
学科分类号：
摘要：
In this paper, the effect of Reynolds number on transonic compressor blade rotor section is investigated. After passing through the first transonic compressor stages , the flow becomes remarkably compressed. In the present work, it is intended to numerically investigate the effects of the inflow Reynolds number on the unique incidence, flow losses, deviation angle, and shock position, at three different important points of "Minimum Loss" and "Choked Flow" in started conditions and "Stall Operation" in un-started conditions.
引用
收藏
页码：2155 / 2165
页数：11
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