Numerical simulation of single-stage transonic compressor with inlet distortion

被引：0
|
作者：
Guo J. [1 ,2 ]
Hu J. [1 ,2 ]
Yin C. [1 ,2 ]
Tu B.-F. [1 ,2 ]
机构：
[1] Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] Collaborative Innovation Center for Advanced Aero-Engine, Beijing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2016年 / 31卷 / 03期
关键词：
Aerodynamic performance; Body force model; Compressor; Inlet distortion; Source term;
D O I：
10.13224/j.cnki.jasp.2016.03.018
中图分类号：
学科分类号：
摘要：
A three-dimensional numerical calculation code called CSAC based on body force model was developed and used to predict fan/compressor performance with inlet distortion. First, the modeling method to build body force model was studied. Then, a three-dimensional numerical calculation code was developed. A single-stage transonic compressor flow field with clean inlet was simulated with the code. The calculation results agreed well with the solutions of Reynolds-averaged Navier-Stokes (RANS) and experimental data. The compressor flow field with inlet steady circumferential total pressure distortion and circumferential total temperature distortion were simulated respectively with the code. The results showed that the flow field with inlet distortion in compressor had large scale and strong three-dimensional features, which led to the decrease of compressor total pressure ratio and stability margin. All results show that this model can effectively analyze the effect of inlet distortion on compressor while reducing the dependency on computational resources and engineering experience. © 2016, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：669 / 677
页数：8
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