Investigation on cooling effectiveness and aerodynamic loss of a turbine cascade with film cooling

• DOI: 10.1007/s11630-016-0833-3
• Publication Date: 2016-01-08T03:45:35Z
• Authors: Jianjun Liu; Xiaochun Lin; Xiaodong Zhang; Baitao An
• Keywords: Pressure-sensitive paint

This paper describes the numerical study on film cooling effectiveness and aerodynamic loss due to coolant and main stream mixing for a turbine guide vane. The effects of blowing ratio, mainstream Mach number, surface curvature on the cooling effectiveness and mixing loss were studied and discussed. The numerical results show that the distributions of film cooling effectiveness on the suction surface and pressure surface at the same blowing ratio (BR) are different due to local surface curvature and pressure gradient. The aerodynamic loss features for film holes on the pressure surface are also different from film holes on the suction surface.