COMPUTATION OF TURBULENT FLOWS AND RADIATED SOUND FROM AXIAL COMPRESSOR CASCADE USING LES

초록

The losses at off-design points from a compressor cascade occur due to the deviation from a design incidence angle at the inlet of cascade. The self-noise from the blade cascade at off-design points comes from a separated boundary layer and vortex sheddings. If the incidence angle to the cascade increases, the stalling in blades may occur and the noise level increases significantly.