Affiliation of Author(s):能源与动力学院

Journal:Hangkong Dongli Xuebao

Abstract: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.

ISSN No.:1000-8055

Translation or Not:no

Date of Publication:2017-06-01

Co-author:Lu, Bo,Wang, Jian,高翔

Correspondence Author:王志强