Влияние относительного окружного расположения статоров на аэроупругое поведение лопаточного венца в полуторной компрессорной ступени

Abstract

Results of the numerical analysis of the aeroelastic behaviour of the vibrating blade row of a compressor stage in a three–dimensional flow of ideal gas whith taking into account aerodynamic interaction stator 0 – a rotor – stator 1 are presented. The numerical method is based on the solution of the coupled problem of non–stationary aerodynamics and blade elastic oscillations for a non–stationary space of gas flow through mutually moving blade rows in a one–and–a–half stage of the axial compressor.