Specifics of the local heat transfer of the accelerated flow along the end-wall of curved turbine passage

Abstract

The experimental study was carried out of the heat transfer of an accelerated flow near the end surface of the curvilinear band formed by the neighboring turbine guide vanes. The level and nature of the change in heat transfer depending on the height of the band and the thickness of the boundary layer at its inlet are revealed. The data obtained can be used for the design and testing of heat exchangers and power equipment.