Abstract:
A numurical model is developed to investigate film cooling in compressible laminar boundary layer flows. This model is applied to the first stagi stator blade of a transonic gas turbine. As a prelude study, film cooling for incompressible flow over a flat plate is also included. Film cooling effectiveness ts reported for a variety of injection configurations so that the effects of .coolant mass flow, rate, injection angle, and slot width can be investigated. For the coolant mass flow rates considered, normal injection provides better cooling than inclined injection. However, normal injection brings about greater boundary layer thickness and may reduce aerodynamic performance. Use of multiple slots provides higher and more uniform effectiveness for the s me coolant mass flow rate.
