Abstract
This paper details experimental and numerical studies on the 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 a high stage loading condition. Hence it becomes important to study methods to control the boundary layer separation. A linear cascade test facility is employed to investigate the aerodynamic performance of the airfoil by use of a miniature Pitot probe. LES simulations are also carried out to gain a better understanding of the flow field around the airfoil. The Reynolds number based on the chord length was varied in the range of 40,000 to 170,000 in order to simulate a typical flight condition. It is found that the proposed methods have a capability to reduce the profile loss and result in improvement of cascade performance.
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