A five-blade, linear cascade is used to experimentally investigate turbine blade platform cooling. A 30deg inclined slot upstream of the blades is used to model the seal between the stator and rotor, and 12 discrete film holes are located on the downstream half of the platform for additional cooling. The film cooling effectiveness is measured on the platform using pressure sensitive paint (PSP). Using PSP, it is clear that the film cooling effectiveness on the blade platform is strongly influenced by the platform secondary flow through the passage. Increasing the slot injection rate weakens the secondary flow and provides more uniform film coverage. Increasing the freestream turbulence level was shown to increase film cooling effectiveness on the endwall, as the increased turbulence also weakens the passage vortex. However, downstream, near the discrete film cooling holes, the increased turbulence decreases the film cooling effectiveness. Finally, combining upstream slot flow with downstream discrete film holes should be cautiously done to ensure coolant is not wasted by overcooling regions on the platform.

Issue Section:
Forced Convection
Keywords:
cooling, film flow, gas turbines, turbulence, vortices, forced convection, film cooling, gas turbine heat transfer
Topics:
Film cooling, Flow (Dynamics), Blades, Coolants, Cooling, Cascades (Fluid dynamics), Turbulence, Pressure
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