Hammerstein–Wiener based reduced-order model for vortex-induced non-linear fluid–structure interaction

2016 ◽  
Vol 33 (2) ◽  
pp. 219-237 ◽  
Author(s):  
Daniele Gallardo ◽  
Onkar Sahni ◽  
Riccardo Bevilacqua
Keyword(s):  
Fluid Structure Interaction ◽  
Reduced Order Model ◽  
Order Model ◽  
Fluid Structure ◽  
Reduced Order ◽  
Structure Interaction ◽  
Non Linear

Extending a Van der Pol Based Reduced-Order Model for Fluid-Structure Interaction Applied to Non-Synchronous Vibrations in Turbomachinery

2021 ◽  
Author(s):  
Richard Hollenbach ◽  
Robert Kielb ◽  
Kenneth Hall
Keyword(s):  
Fluid Structure Interaction ◽  
Reduced Order Model ◽  
Van Der Pol Oscillator ◽  
Previous Model ◽  
Stable Limit ◽  
Order Model ◽  
Van Der Pol ◽  
Fluid Structure ◽  
Reduced Order ◽  
Structure Interaction

Abstract This paper expands upon a multi-degree-of-freedom, Van der Pol oscillator used to model buffet and Nonsynchronous Vibrations (NSV) in turbines. Two degrees-of-freedom are used, a fluid tracking variable incorporating a Van der Pol oscillator and a classic spring, mass, damper mounted cylinder variable; thus, this model is one of fluid-structure interaction. This model has been previously shown to exhibit the two main aspects of NSV. The first is the lock-in or entrainment phenomenon of the fluid shedding frequency jumping onto the natural frequency of the oscillator, while the second is a stable limit cycle oscillation (LCO) once the transient solution disappears. Improvements are made to the previous model to better understand this aeroelastic phenomenon. First, an error minimizing technique through a system identification method is used to tune the coefficients in the Reduced Order Model (ROM) to improve the accuracy in comparison to experimental data. Secondly, a cubic stiffness term is added to the fluid equation; this term is often seen in the Duffing Oscillator equation, which allows this ROM to capture the experimental behavior more accurately, seen in previous literature. The finalized model captures the experimental cylinder data found in literature much better than the previous model. These improvements also open the door for future models, such as that of a pitching airfoil or a turbomachinery blade, to create a preliminary design tool for studying NSV in turbomachinery.

scholarly journals A High Efficient Fluid-Structure Interaction Method for Flutter Analysis of Mistuned

2018 ◽  
Vol 36 (5) ◽  
pp. 856-864
Author(s):  
Zhanhe Liu ◽  
Jinlou Quan ◽  
Jingyuan Yang ◽  
Dan Su ◽  
Weiwei Zhang
Keyword(s):  
Fluid Structure Interaction ◽  
Reduced Order Model ◽  
Interaction Method ◽  
Order Model ◽  
Fluid Structure ◽  
Reduced Order ◽  
Structure Interaction ◽  
Bladed Disk ◽  
High Efficient ◽  
Flutter Analysis

The time cost is very high by direct fluid-structure interaction method for mistuned bladed disk structures, so aerodynamic loads generally are ignored or treated as small perturbations in traditional flutter analysis. In order to analyze the flutter characteristics of mistuned blade rapidly and accurately, this paper presents an efficient fluid-structure interaction method based on aerodynamic reduced order model. system identification technology and two basic assumptions are used to build the unsteady aerodynamic reduced order model. Coupled the structural equations and the aerodynamic model in the state space, the flutter stability of mistuned bladed disk can be obtained by changing the structural parameters. For the STCF 4 example, the response calculated by this method agrees well with the results obtained by the direct CFD, but the computational efficiency is improved by nearly two orders of magnitude. This method is used to study the stiffness mistuned cascade system, and the stability characteristics of the system are obtained by calculating the eigenvalues of the aeroelastic matrix. The results show that the stiffness mistuning can significantly improve the flutter stability of the system, and also lead to the localization of the mode. The mistuning mode, mistuning amplitude and fluid structure interaction can influence the flutter stability obviously.

EXTENDING A VAN DER POL BASED REDUCED-ORDER MODEL FOR FLUID-STRUCTURE INTERACTION APPLIED TO NON-SYNCHRONOUS VIBRATIONS IN TURBOMACHINERY

2021 ◽  
pp. 1-14
Author(s):  
Richard Hollenbach ◽  
Robert Kielb ◽  
Kenneth Hall
Keyword(s):  
Fluid Structure Interaction ◽  
Reduced Order Model ◽  
Van Der Pol Oscillator ◽  
Previous Model ◽  
Stable Limit ◽  
Order Model ◽  
Van Der Pol ◽  
Fluid Structure ◽  
Reduced Order ◽  
Structure Interaction

Abstract This paper expands upon a multi-degree-of-freedom, Van der Pol oscillator used to model buffet and Nonsynchronous Vibrations (NSV) in turbines. Two degrees-of-freedom are used, a fluid tracking variable incorporating a Van der Pol oscillator and a classic spring, mass, damper mounted cylinder variable; thus, this model is one of fluid-structure interaction. This model has been previously shown to exhibit the two main aspects of NSV. The first is the lock-in or entrainment phenomenon of the fluid shedding frequency jumping onto the natural frequency of the oscillator, while the second is a stable limit cycle oscillation (LCO) once the transient solution disappears. Improvements are made to the previous model to better understand this aeroelastic phenomenon. First, an error minimizing technique through a system identification method is used to tune the coefficients in the Reduced Order Model (ROM) to improve the accuracy in comparison to experimental data. Secondly, a cubic stiffness term is added to the fluid equation; this term is often seen in the Duffing Oscillator equation, which allows this ROM to capture the experimental behavior more accurately, seen in previous literature. The finalized model captures the experimental cylinder data found in literature much better than the previous model. These improvements also open the door for future models, such as that of a pitching airfoil or a turbomachinery blade, to create a preliminary design tool for studying NSV in turbomachinery.

scholarly journals Nonlinear reduced-order model for vertical sloshing by employing neural networks

2021 ◽  
Author(s):  
Marco Pizzoli ◽  
Francesco Saltari ◽  
Franco Mastroddi ◽  
Jon Martinez-Carrascal ◽  
Leo M. González-Gutiérrez
Keyword(s):  
Neural Network ◽  
Fluid Structure Interaction ◽  
Oscillation Amplitude ◽  
Reduced Order Model ◽  
Order Model ◽  
Data Set ◽  
Fluid Structure ◽  
Reduced Order ◽  
Structure Interaction ◽  
Bouncing Ball

AbstractThe aim of this work is to provide a reduced-order model to describe the dissipative behavior of nonlinear vertical sloshing involving Rayleigh–Taylor instability by means of a feed forward neural network. A 1-degree-of-freedom system is taken into account as representative of fluid–structure interaction problem. Sloshing has been replaced by an equivalent mechanical model, namely a boxed-in bouncing ball with parameters suitably tuned with performed experiments. A large data set, consisting of a long simulation of the bouncing ball model with pseudo-periodic motion of the boundary condition spanning different values of oscillation amplitude and frequency, is used to train the neural network. The obtained neural network model has been included in a Simulink®  environment for closed-loop fluid–structure interaction simulations showing promising performances for perspective integration in complex structural system.

scholarly journals Adaptive reduced-order modeling for non-linear fluid-structure interaction

2021 ◽  
pp. 105099
Author(s):  
Ali Thari ◽  
Vito Pasquariello ◽  
Niels Aage ◽  
Stefan Hickel
Keyword(s):  
Fluid Structure Interaction ◽  
Reduced Order Modeling ◽  
Fluid Structure ◽  
Reduced Order ◽  
Structure Interaction ◽  
Non Linear

Fluid-Structure Interaction Using a Modal Approach

2011 ◽  
Author(s):  
F. Debrabandere ◽  
B. Tartinville ◽  
Ch. Hirsch ◽  
G. Coussement
Keyword(s):  
Fluid Structure Interaction ◽  
Axial Compressor ◽  
Linear Structure ◽  
Mode Shapes ◽  
Order Model ◽  
Modal Approach ◽  
Fluid Structure ◽  
Flow Solver ◽  
Reduced Order ◽  
Structure Interaction

A new method for Fluid-Structure Interaction (FSI) predictions is here introduced, based on a Reduced-Order Model (ROM) for the structure, described by its mode shapes and natural frequencies. A linear structure is assumed as well as Rayleigh damping. A two-way coupling between the fluid and the structure is ensured by a loosely-coupling staggered approach: the aerodynamic loads computed by the flow solver are used to determine the deformations from the modal equations, which are sent back to the flow solver. The method is firstly applied to a clamped beam oscillating under the effect of von Karman vortices. The results are compared to a full-order model. Then a flutter application is considered on the AGARD wing 445.6. Finally, the modal approach is applied to the aeroelastic behavior of an axial compressor stage. The influence of passing rotor blade wakes on the downstream stator blades is investigated.

Fluid–Structure Interaction Using a Modal Approach

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
F. Debrabandere ◽  
B. Tartinville ◽  
Ch. Hirsch ◽  
G. Coussement
Keyword(s):  
Fluid Structure Interaction ◽  
Axial Compressor ◽  
Linear Structure ◽  
Mode Shapes ◽  
Order Model ◽  
Modal Approach ◽  
Fluid Structure ◽  
Flow Solver ◽  
Reduced Order ◽  
Structure Interaction

A new method for fluid‐structure interaction (FSI) predictions is here introduced, based on a reduced-order model (ROM) for the structure, described by its mode shapes and natural frequencies. A linear structure is assumed as well as Rayleigh damping. A two-way coupling between the fluid and the structure is ensured by a loosely coupling staggered approach: the aerodynamic loads computed by the flow solver are used to determine the deformations from the modal equations, which are sent back to the flow solver. The method is first applied to a clamped beam oscillating under the effect of von Karman vortices. The results are compared to a full-order model. Then a flutter application is considered on the AGARD wing 445.6. Finally, the modal approach is applied to the aeroelastic behavior of an axial compressor stage. The influence of passing rotor blade wakes on the downstream stator blades is investigated.

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