Numerical simulation on blade tip unsteady flow in transonic compressor rotor

被引：0

作者：

Lu, Bo ^{[1
]}

Wang, Zhiqiang ^{[1
]}

Wang, Jian ^{[2
]}

Gao, Xiang ^{[1
]}

机构：

[1] Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing,210016, China

[2] South Industry Limited Corporation, Aero Engine (Group) Corporation of China, Zhuzhou,Hunan,412002, China

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2017年 / 32卷 / 06期

关键词：

Transonic flow - Turbomachine blades - Compressors - Mass transfer - Leakage (fluid) - Numerical models - Unsteady flow;

D O I：

10.13224/j.cnki.jasp.2017.06.026

中图分类号：

学科分类号：

摘要：

The detailed three-dimensional unsteady numerical study was conducted in a transonic compressor rotor to deepen the understanding of unsteady flow phenomenon in rotor blade tip region. Unsteady numerical simulations were studied in single rotor under different inlet conditions and different mass flows, so as to investigate the complex flow structure in rotor blade tip region and the development of blade tip unsteady flow. Results showed that the structure of blade tip flow field varied under different inlet conditions. When inlet direction was non-axial, signal passage periodical form emerged for unsteady flow at blade tip, while an unsteady flow phenomenon like rotating instability, spreading along circumferential direction, occurred in blade tip region under axial inlet condition. And with the decrease of mass flow, the structural flow field of blade tip region changed correspondingly. © 2017, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：1481 / 1490