This paper aims to numerically investigate the flow characteristics and heat transfer coefficient distribution over high-pressure gas turbine rotor blades mounted in a twodimensional linear cascade arrangement. The heat transfer characteristics are evaluated at various transonic blade exit Mach numbers and blade incidence angles. The study also aims to enhance the fundamental understanding of the flow characteristics along the gas turbine blade passage at transonic flow conditions. Major flow characteristics such as the shock wave position, flow separation and reattachment, laminar to turbulent boundary layer transition, and shock - boundary layer interactions were investigated by varying the blade exit Mach number (0.85 to 1.30) and incidence angle (-15° to 15°). It is observed that as the blade incidence angle is increased from -15° to 15°, the Mach number rapidly increases along the blade suction side. Increasing the exit Mach number resulted in increased shock strength and more intense shock - boundary layer interaction.