Flutter analysis of bending-torsion coupling of aero-engine compressor blade with assembled clearance

Gang Han; Yushu Chen; Xiaodong Wang

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Flutter analysis of bending-torsion coupling of aero-engine compressor blade with assembled clearance

机译：装配间隙的航空发动机压气机叶片弯扭耦合颤振分析

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In this paper, the flutter of a compressor blade is investigated to explore the fracture failure mechanism of the blade with an assembled clearance, cubic structural nonlinearity and aerodynamic forces. Firstly, the stability of the linearized system is studied in the neighborhood of an equilibrium point and the threshold speed of the linear flutter of the blade is obtained. Then the response equations of limit cycle oscillations (LCOs) are deduced by using the averaging method, and the stability of LCOs is analyzed based on the first-order approximate theory. Comparisons with the results from the fourth-order Runge-Kutta scheme are carried out, and the accuracy of the first-order approximation of the averaging method is discussed. Finally, the influence of clearance parameter, bending stiffness and torsional rigidity on the flutter characteristics of the blade is analyzed.

机译：本文研究了压气机叶片颤振，探讨了具有间隙，立方结构非线性和空气动力的叶片断裂破坏机理。首先，在平衡点附近研究了线性化系统的稳定性，并获得了叶片线性颤动的阈值速度。然后，采用平均法推导极限循环振荡的响应方程，并基于一阶近似理论分析了其稳定性。进行了与四阶Runge-Kutta方案的结果的比较，并讨论了平均方法的一阶近似的准确性。最后，分析了间隙参数，弯曲刚度和扭转刚度对叶片颤振特性的影响。

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来源
《Applied Mathematical Modelling》 |2015年第9期|2539-2553|共15页
作者
Gang Han; Yushu Chen; Xiaodong Wang;
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作者单位

School of Astronautics, Harbin Institute of Technology, PO Box 137, Harbin 150001, China;

School of Astronautics, Harbin Institute of Technology, PO Box 137, Harbin 150001, China;

School of Astronautics, Harbin Institute of Technology, PO Box 137, Harbin 150001, China;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类
关键词
Compressor blade; Assembled clearance; Bending-torsion coupling flutter; Limit cycle oscillations; Amplitude jumping phenomenon;

机译：压气机叶片组装间隙;弯扭耦合颤振;限制循环振荡;幅度跳跃现象;

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1. Principal resonance bifurcation of bending-torsion coupling of aero-engine compressor blade with assembled clearance under lateral displacement excitation of rotor shaft [J] . Gang Han, Yushu Chen Nonlinear dynamics . 2014,第3期

机译：转子轴侧向位移激励下具有间隙间隙的航空发动机压气机叶片弯扭联轴器的主共振分叉
2. Mathematical Modeling and Analysis of Flutter in Bending-Torsion Coupled Beams, Rotating Blades, and Hard Disk Drives [J] . Marianna A. Shubov Journal of aerospace engineering . 2004,第2期

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3. Blade Tip Clearance Flow and Compressor Nonsynchronous Vibrations: The Jet Core Feedback Theory as the Coupling Mechanism [J] . Jean Thomassin, Huu Duc Vo, Njuki W. Mureithi Journal of turbomachinery . 2009,第1期

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4. Sensitive Flutter Parameters Analysis with Respect to Flutter-Free Design of Compressor Blade [C] . Sun Hai, Yang Lin, Li Hongxin Asia-Pacific International Symposium on Aerospace Technology . 2015

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5. Axial compressor blade design for desensitization of aerodynamic performance and stability to tip clearance. [D] . Erler, Engin. 2013

机译：轴流压气机叶片设计可降低空气动力性能并保持叶尖间隙的稳定性。
6. Rotating Stall Induced Non-Synchronous Blade Vibration Analysis for an Unshrouded Industrial Centrifugal Compressor [O] . Xinwei Zhao, Qiang Zhou, Shuhua Yang, 2019

机译：无罩工业离心压缩机的旋转失速诱导非同步叶片振动分析
7. Sensitive Flutter Parameters Analysis with Respect to Flutter-free Design of Compressor Blade [O] . Hai Sun, Lin Yang, Hongxin Li 2015

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Flutter analysis of bending-torsion coupling of aero-engine compressor blade with assembled clearance

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