Abstract
This study aims at the development of a new method to increase aerodynamic loading of low-pressure turbine airfoils for
modern aeroengines to a great extent for the sake of drastic reduction of their airfoil counts. This study proposes a twodimensional
device on the airfoil suction surface to suppress the separation bubble that causes large aerodynamic loss, especially
at low Reynolds number condition. This paper describes experimental investigations on aerodynamic performance of
the airfoils with the device under steady-state flow conditions. The main objective of this paper is to show how and to what
extent the device without any other disturbances affects the suction surface boundary layer accompanying separation buble.
It turns out from the detailed experiments that the device on the airfoil surface can effectively suppress the separation
bubble, resulting in significant improvement of cascade aerodynamic performance.
