The present work is part of a comprehensive heat transfer and ﬁlm-cooling study on a locally cooled non-axisymmetric contoured turbine endwall. A new test rig consisting of a linear cascade of three prismatic vanes at unity scale and exchangeable endwall has been established. The rig is operated in an open-loop conﬁguration at a reduced main gas temperature of 425 K, an exit Mach number of 0.5, and an exit Reynolds number of 1.6×10^6. Air is used both as main gas and coolant; a realistic density ratio is achieved by cooling the coolant below freezing. In Part I  of the study aerodynamic measurements are presented. This paper concentrates on ﬁlm-cooling of the contoured endwall with special emphasis on data acquisition and reduction for the application of the superposition principle of ﬁlm cooling. First experimental results from thermographic measurements are discussed.
A New Test Facility to Investigate Film Cooling on a Non-Axisymmetric Contoured Turbine Endwall, Part II: Heat Transfer and Film Cooling Measurements
ASME Turbo Expo 2015
15.06.2015 - 19.06.2015
Paper No.: GT2015-42524