Abstract
This paper details experimental and numerical studies on effectiveness in controlling boundary layer separation with the performance of dimples on a low-pressure turbine airfoil. The profile loss due to boundary layer separation in LPT has a significant contribution to its overall loss, especially in high stage loading case. Hence it becomes important to study control methods of the boundary layer separation. The aerodynamic performance of the airfoil is investigated in a linear cascade test facility. The boundary layer on the suction surface is measured using a hot wire probe. RANS simulations are also carried out to gain a better understanding of the flow field around the airfoil. The experiments show that the proposed method can reduce the size of the separated flow region, and the numerical simulations reveal the vortical structure caused by the dimples on the suction surface.
