Influence of rotor-stator interaction on rotor blade flutter characteristics

被引：0
|
作者：
Yang H. [1 ,2 ]
Li Z. [1 ,2 ]
机构：
[1] Collaborative Innovation Center for Advanced Aero-Engine, Beijing
[2] School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing
来源：
Yang, Hui (huiyang@buaa.edu.cn) | 1600年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 42期
关键词：
Aerodynamic damping; Blade flutter; Fluid-structure interaction; Full-annulus multi-row; Rotor-stator interaction; Travelling wave vibration;
D O I：
10.13700/j.bh.1001-5965.2015.0094
中图分类号：
学科分类号：
摘要：
A full-annulus multi-row coupled fluid-structure simulation on a certain high pressure compressor was conducted by an in-house program to analyze the influence of inlet guide vane (IGV) on rotor blade flutter stability in different operation conditions and geometry models. The effectiveness of the program in the field of turbomachinery flutter was verified by numerically simulating the aeroelastic standard configuration 4 for the IGV-rotor model and isolated rotor model respectively, detailed fluid-structure interaction analyses were performed at near choked, near design and near stall operation points to assess the effect of nodal diameter on the flutter stability. The least unstable vibration form of blade can be presented. By the comparison of the results, the influence of IGV varies with the operation conditions. At the near choked point, the rotor aerodynamic damping of the first bending mode increases by 130.63% via the IGV. The results indicate that the existence of the guide vane causes the unsteady pressure wave reflection, which can enhance the unsteady oscillating pressure amplitudes on the rotor blade surface and improve the flutter stability of the bending mode. Flutter analyses based on isolated rotor model will give inaccurate aerodynamic damping values. © 2016, Beijing University of Aeronautics and Astronautics (BUAA). All right reserved.
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页码：258 / 264
页数：6
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