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MKP 3D MODELOVÁNÍ TEPELNÝCH DĚJŮ TLUMÍCÍCH PRVKŮ S TERMO-MECHANICKOU VAZBOU
Pešek, Luděk ; Šulc, Petr
The COMSOL code based on weak formulation of PDE's problem was used for solution of thermo-mechanical interaction in pre-pressed rubber segment used for resilient elements of the composed tram wheels. For computational time efficiency the structural and heat field are decomposed and the balance of heat power density and dissipation power density realizes the coupling. The dissipation power is computed according to the assumed proportional damping model. The results of thermo-mechanical processes for press and shear deformations under static pre-pressed and cyclic dynamic loading are presented and analyzed.
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Numerické řešení stacionárního a nestacionárního stlačitelného viskozního proudění v kanále
Punčochářová, P. ; Kozel, Karel ; Horáček, Jaromír ; Fürst, J.
This study deals with numerical solution of 2D unsteady flow of compressible viscous fluid in channel for a low inlet airflow velocity. The unsteadiness of the flow is caused by a prescribed periodic motion of a part of the channel wall with large amplitudes. The channel is harmonically opening and nearly closing. When closing the airlow velocity is becoming much higher in the narrowest part of the airways, where also the viscous forces play important role. Therefore for a correct modelling of a real flow the compressible, viscous and unsteady fluid-flow model decribed by Navire-Stokes equations should be considered. The authors present the simulations of the flow field by the expecially developed program.
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Nelineární zpětná vazba mezi nestlačitelným prouděním a kmitáním profilu se třemi stupni volnosti
Růžička, M. ; Feistauer, M. ; Sváček, P. ; Horáček, Jaromír
In this article we are concerned with the numerical solution of an aeroelastic problem of two dimensional viscous incompressible flow around an airfoil with three degrees of freedom in a wind tunnel the airfoil is represented by a solid body, which can perform vertical and torsional vibrations and its flap can rotate with respect to the airfoil. Model of the flow is formed by two-dimensional Navier-Stokes equations and the continuity equation. Stabilized finite element method is used for obtaining a numerical solution. Due to the motion of the airfoil the computational domain is time-dependent.
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