scholarly journals Experiments on transonic limit-cycle-flutter of a flexible swept wing

2019 ◽  
Vol 84 ◽  
pp. 153-170
Author(s):  
Günter Schewe ◽  
Holger Mai
Keyword(s):  
Limit Cycle ◽  
Swept Wing ◽  
Limit Cycle Flutter

Analysis of Flutter-Induced Limit Cycle Oscillations in Gas-Turbine Structures With Friction, Gap, and Other Nonlinear Contact Interfaces

2012 ◽  
Vol 134 (6) ◽  
Author(s):  
E. P. Petrov
Keyword(s):  
Gas Turbine ◽  
Limit Cycle ◽  
Large Scale ◽  
Direct Calculation ◽  
Aerodynamic Characteristics ◽  
Frequency Domain Method ◽  
Nonlinear Contact ◽  
Limit Cycle Flutter ◽  
Interface Parameters ◽  
First Time

A frequency-domain method has been developed to predict and comprehensively analyze the limit-cycle flutter-induced vibrations in bladed disks and other structures with nonlinear contact interfaces. The method allows, for the first time, direct calculation of the limit-cycle amplitudes and frequencies as functions of contact interface parameters and aerodynamic characteristics using realistic large-scale finite element models of structures. The effects of the parameters of nonlinear contact interfaces on limit-cycle amplitudes and frequencies have been explored for major types of nonlinearities occurring in gas-turbine structures. New mechanisms of limiting the flutter-induced vibrations have been revealed and explained.

Limit Cycle Flutter Analysis of Plate-Type Beam with Dissymmetrical Subsection Linear Stiffness

2011 ◽  
Vol 66-68 ◽  
pp. 1732-1737
Author(s):  
Li Lu ◽  
Yi Ren Yang ◽  
Chen Guang Fan ◽  
Ming Lu Zhang
Keyword(s):  
Galerkin Method ◽  
Viscous Flow ◽  
Limit Cycle ◽  
Equivalent Linearization ◽  
Incompressible Viscous Flow ◽  
Flutter Analysis ◽  
Limit Cycle Flutter ◽  
The Stability ◽  
Theoretical Results ◽  
Plate Type

The limit cycle flutter of a plate-type structure with dissymmetrical subsection linear stiffness in incompressible viscous flow was studied. Galerkin Method was used to get the differential equations of system. The equivalent linearization concept was performed to predict the ranges of limit cycle flutter velocities. The flutter borderline map was used to analyze the the stability of limit cycle flutter. By numerical integrating, the velocities of convergence, flutter and instability were obtained. The theoretical results agree well with the results of numerical integration.

Efficient Method for Limit Cycle Flutter Analysis Based on Nonlinear Aerodynamic Reduced-Order Models

AIAA Journal ◽  
2012 ◽  
Vol 50 (5) ◽  
pp. 1019-1028 ◽  
Author(s):  
Weiwei Zhang ◽  
Bobin Wang ◽  
Zhengyin Ye ◽  
Jingge Quan
Keyword(s):  
Limit Cycle ◽  
Efficient Method ◽  
Reduced Order Models ◽  
Reduced Order ◽  
Flutter Analysis ◽  
Limit Cycle Flutter ◽  
Nonlinear Aerodynamic
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