Characteristics of heat transfer on a turbine blade endwall under various inlet flow conditions

The assembly step between the vane and blade in a gas turbine exists because of the rotating blade and expansion of the external flow passage. The assembly step has a great impact on the heat transfer distribution on the endwall. In this study, a rod was installed in front of the blade to generate non-uniform inlet flow and to observe the heat transfer characteristics on the endwall. The mass transfer coefficients on the endwall were measured using the naphthalene sublimation method. The results revealed that, as the diameter of the rod increased, a turbulent boundary layer developed.