Abstract. In this paper the occurrence of flutter in a simplified blade cascade is analysed. The simplified blade cascade is formed by three flat plates, which perform a kinematic harmonic motion, each with a different inter-blade phase angle. The inter-blade phase angles are chosen in order for travelling wave mode of vibration to be present. The aim of the simulations is to determine the aerodynamic damping coefficients caused by the aerodynamic forces acting on the flat plates, which show whether flutter occurs. The non-linear system of Favre-averaged NavierStokes equations in ALE formulation completed by the Spalart-Allmaras turbulence model was chosen as the mathematical model. The simulations were performed using the developed inhouse CFD software based on the discontinuous Galerkin method, which offers high order of accuracy.
In this paper, a numerical simulation and experimental measurements of compressible viscous fluid flow in simplified blade cascade are compared. The cascade consists of five flat plates three of which perform prescribed harmonic motion. The computed unsteady velocity field is compared with experimental measurements at selected points. Moreover, the power spectral density corresponding to the frequency of harmonic motion is computed for both the numerical and experimental data and compared. The numerical simulation was performed using the developed in-house CFD software based on the discontinuous Galerkin method, which offers high order of accuracy.
Abstract. In this paper, a numerical simulation and experimental measurements of compressible viscous fluid flow in simplified blade cascade are compared. The cascade consists of five flat plates three of which perform prescribed harmonic motion. The computed unsteady velocity field is compared with experimental measurements at selected points. Moreover, the power spectral density corresponding to the frequency of harmonic motion is computed for both the numerical and experimental data and compared. The numerical simulation was performed using the developed in-house CFD software based on the discontinuous Galerkin method, which offers high order of accuracy.
The present study applies the discontinuous Galerkin finite element method to a numerical simulation of a compressible fluid flow through a labyrinth seal. This paper is proposes a curvilinear hexahedral element, which is deformed in such a way that it matches the rotated walls of the labyrinth seal exactly. A numerical study is performed on the staggered labyrinth seal with two teeth on the rotor and one tooth on the stator. For numerical simulation, three computational meshes with different refinement are considered. All of the numerical simulations are performed for both stationary rotor and for rotor rotating at 50 Hz. The obtained numerical results are compared with results computed by the commercial CFD software Ansys Fluent.
This paper deals with flow field prediction in a blade cascade using the convolution neural network. The convolutional neural network (CNN) predicts density, pressure and velocity fields based on the given geometry. The blade cascade is modeled as a single interblade channel with periodic boundary conditions. In this paper, an algorithm that enforces periodic boundary conditions onto the CNN is presented. The main target of this study is to parametrize the CNN model depending on the Reynolds number. A new parametrization approach based on a so-called hypernetwork is employed for this purpose. The idea of this approach is that when the Reynolds number is modified, the hypernetwork modifies the weights of the CNN in such a way that it produces flow fields corresponding to that particular Reynolds number. The concept of the hypernetwork-based parametrization is tested on the problem of a compressible fluid flow through a blade cascade with variable blade profiles and Reynolds numbers.
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