Coupling Technique of Rotor-Fuselage Dynamic Analysis

Tang, Dunbing; Wang, M. Q.

doi:10.1115/1.3269174

Cited by 5 publications

(2 citation statements)

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“…The effect of stagger angle on the inertial and elastic coupling in bladed disks was reported by Crawley and Mokadam (1984). Tang and Wang (1984) reported a model for rotor fuselage dynamic analysis. Loewy and Khader (1984) studied the effect of flexural shaft flexibility on the dynamics of bladed-disk assemblies.…”

Section: Introductionmentioning

confidence: 93%

Stability Analysis of Rotating Blade Vibration due to Torsional Excitation

Al‐Nassar

Kalyon

Pakdemi̇rli̇

et al. 2007

Journal of Vibration and Control

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This paper presents an approximate analysis of the vibration stability of a rotating blade due to shaft torsional vibration excitation. The governing equation adopted in the study is a Hill's type linear second order ordinary differential equation with multiple harmonically variable coefficient terms. The strained parameters method, a perturbation technique, is utilized in developing the stability transition curves in the plane of parameters related to the rotor speed, the torsional vibration excitation frequency and the blade natural frequency. The stable and unstable regions obtained by perturbations are contrasted to those obtained by numerical stability analysis performed using Floquet theory and an excellent match is observed for small torsional vibration amplitudes. Numerical integration of the original equation at selected points in the predicted stable and unstable regions showed that the predicted behavior of the responses is correct, wherein the unstable regions growing blade vibration is exhibited.

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Section: Introductionmentioning

confidence: 93%

Stability Analysis of Rotating Blade Vibration due to Torsional Excitation

Al‐Nassar

Kalyon

Pakdemi̇rli̇

et al. 2007

Journal of Vibration and Control

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show abstract

“…The effect of stagger angle on the inertial and elastic coupling in bladed disks was reported by Crawley and Mokadam [2]. Tang and Wang [3] proposed a model for rotor fuselage dynamic analysis. The problem of blade vibration and its interaction with the main rotor torsional vibration was studied by Okabe et al [4].…”

Section: Introductionmentioning

confidence: 90%

Stability Analysis of Rotating Blade Vibrations Using Lyapunov Exponents

Kunduracı¹

2018

El-Cezeri Fen Ve Mühendislik Dergisi

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This paper presents an analysis of the vibration stability of a rotating blade due to shaft torsional vibration excitation. The governing equation adopted in the study is a Hill's type linear second order ordinary differential equation with multiple harmonically variable coefficient terms. The differential equation of the system is rewritten as two coupled first order ordinary differential equations. The stable and unstable regions are determined by the Lyapunov characteristics exponents on parameter space (grid) relating to the rotor speed, the torsional vibration excitation frequency and the blade natural frequency. The results are contrasted to those obtained by the strained parameter method (a perturbation technique), an excellent match is observed for small torsional vibration amplitudes .

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Stability analysis of rotating blade bending vibration due to torsional excitation

Al‐Bedoor

Al-Qaisia

2005

Journal of Sound and Vibration

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Coupling Technique of Rotor-Fuselage Dynamic Analysis

Cited by 5 publications

References 0 publications

Stability Analysis of Rotating Blade Vibration due to Torsional Excitation

Stability Analysis of Rotating Blade Vibration due to Torsional Excitation

Stability Analysis of Rotating Blade Vibrations Using Lyapunov Exponents

Stability analysis of rotating blade bending vibration due to torsional excitation

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