Численный анализ аэроупругого поведения лопаточного венца осевой турбомашины

Abstract

There presented numerical analysis for the aeroelastic behaviour of the oscillations blade row in axial turbomachine in 3D ideal gas flow with coupled problem of a aerodynamics and elastic blades oscillations. The numerical analysis of the associated blade oscillation aerodamping confirmed the interaction of the first six eigen modes.