Численный анализ нестационарных нагрузок и аэроупругих колебаний лопаточного венца последней ступени турбомашины с учетом неравномерного в окружном направлении противодавления

Abstract

There performed the results of numerical analysis of the aeroelastic behaviour of a vibrating blade row of the turbine stage in a three-dimensional flow of an ideal gas, taking into account non-uniform of the pressure distribution in the circumferential direction. A numerical method is based on the solution of the coupled problem of the non-stationary aerodynamics and elastic vibrations of blades for non-stationary spatial gas flow through the blade rows of the last stage axial turbine.