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3 Transactions of the Institute of Fluid-Flow Machinery

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Experimental investigation of palisade flutter for the harmonic oscillations

100%

Tsyimbalyuk V. , Zinkowskij A. , Rządkowski R.

Transactions of the Institute of Fluid-Flow Machinery

2005

tom nr 116

3-26

The experimental stand for the flutter analysis was described. In this stand one can measure simultaneously unsteady aerodynamic force and moment with arbitrary combinations of bending and torsion motions of airfoil cascades in the subsonic flow. The cascade is composed of nine blades, four of them are vibrating. Unsteady flow effects have been investigated for subsonic flow in a compressor cascade. Specifically, experimental forced bending and torsion vibration were performed. The aerodynamic work coefficient of bending and torsional cascade vibrations for different interblade phase angles, Strouhal Numbers, and the incidence angles were shown.

3D inviscid flutter of IV Standard Configuration. Part II. Coupled fluid-structure oscilstions

100%

Rządkowski R. , Gnesin V.

tom nr 111

51-71

A three-dimensional nonlinear time-marching method and numerical analysis for aerolastic behaviour of oscillating blade of the IV Standard Configuration has been presented. The approach is based on the solution of the coupled fluid-structure problem in which the aerodynamic and structural equations are integrated simultaneously in time. In this formulation of a coupled problem, the interblade phase angle at which stability (or instability) would occur, is a part of the solution. The ideal gas flow through multiple interblade passage (with periodicity on the whole annulus) is described by the unsteady Euler equations in the form of conservative laws, which are integrated by use of the explicit monotonous second order accurate Godunov-Kolgan finite volume scheme and moving hybrid H-H (or H-O) grid. The structure analysis uses the modal approach and 3D finite element model of the blade. The blade motion is assumed to be a linear combination of mode shapes with the modal coefficients depending on time. The influence of the natural frequencies on the aerolastic coupled oscillations for the Fourth Standard Configuration is shown. It has been shown that interaction between modes plays an important role in the aerolastic blade response. This interaction has essentially nonlinear character and leads to blade limit cycle oscillations. The sign of the aerodamping coefficient calculated for the harmonic oscillations, may be considered only as a necessary, but not a sufficient condition for self-exited oscillations.

3D inviscid flutter of IV Standard Configuration. Part.I. Harmonic oscillations

100%

Gnesin V. , Rządkowski R.

tom nr 111

37-50

A three-dimensional nonlinear time-marching method and numerical analysis for aerolastic behaviour of oscillating blade row of the IV Standard Configuration has been presented. The approach is based on the solution of the coupled fluid-structure problem in which the aerodynamic and structural equations are integrated simultaneously in time. In this formulation of a coupled problem, the interblade phase angle at which stability (or instability) would occur, is a part of the solution. The ideal gas flow through multiple interblade passage (with periodicity on the whole annulus) is described by the unsteady Euler equations in the form of conservative laws, which are integrated by use of the explicit monotonous second order accurate Godunov-Kolgan finite volume scheme and a moving hybrid H-H (or H-O) grid. The structure analysis uses the modal approach and 3D finite element model of the blade. The blade motion is assumed to be a linear combination of modes shapes with the modal coefficients depending on time. The influence of the natural frequencies on the aerodynamic for the Fourth Standard Configuration is shown. The instability regions for the first two modes shapes and the distribution of the aerodamping coefficient along blade length were shown for a harmonic oscillation with the assumed interblade phase angle.