Influence of aerodynamic parameters on the heat transfer in gas turbine blade cascade

A technique was developed to obtain the local heat transfer coefficient under constant heat flux boundary condition.13; Initial experiments were done on a model cylinder to ascertain the accuracy of the technique. Subsequently a turbine blade model was fabricated with 22 surface, thermocouples, experiments were conducted in a two dimensional subsonic cascade tunnel (Tunnel A) with a five bladed cascade assembly. The heat transfer blade was located in the middle. In addition the surface pressure distribution was also obtained by replacing the heat transfer blade by a blade model with 20 surface pressure tapping