Abstract The aim of the current project is to study transitional incompressible flow on low pressure turbine blade by large eddy simulation. The T106A cascade geometry is chosen. Reynolds number based on the inlet velocity and axial chord length is 1.1×〖10〗^5. The dynamic Smagorinsky subgrid model is chosen. In this model constant C, is dynamically computed based on the information provided by the resolved scales of motion and behaves better than the Smagorinsky model in near wall and shear layer regions. Lid driven cavity and backward facing step problems have been investigated for eva‎luating accuracy of the numerical code and the results show very good agreement with experimental data. Time averaged static pressure coefficient on blade’s suction side and pressure side shows a reasonable agreement with experiment results. Separation, transition and reattachment phenomena have been studied. Boundary layer separation occurs at 87% axial chord. Finally the flow in the boundary layer undergoes transition to turbulence and reattachment point occurs at 98% axial chord.

بهمن اسدي