Simulation of secondary flows in turbomachinery by the discontinuous Galerkin method

Secondary flows have a huge impact on the losses in low pressure gas turbines and the inlet boundary layer state is one of the factors which most affects the endwall flow field. The present work aims at investigating secondary flows in a low-pressure gas turbine cascade by means of RANS simulations for two different inlet conditions. The equations are discretised in space by the Discontinuous Galerkin method and implicit time integration is adopted. Changes in the peculiarities of the flow field within the cascade passage are discussed. The results are compared with experimental and numerical data available in the literature.