This paper is focused on the effect of film-hole configurations on platform film cooling. The
platform is cooled by purge flow from a simulated stator-rotor seal combined with discrete …

Turbine vanes are typically assembled as a section containing single or double airfoil units
in an annular pattern. First stage guide vane assembly results in two common mating …

Film cooling effectiveness measurements under rotation were performed on the rotor blade
platform using a pressure sensitive paint (PSP) technique. The present study examines, in …

Fan-shaped film-cooling holes have been shown to provide superior cooling performance to
cylindrical holes along flat plates and turbine airfoils over a large range of different …

The complex large scale coherent vortex systems which originate and develop through the
endwall passage have strong interaction with the film cooling flows near the endwall. Two …

Detailed characteristics of film cooling from discrete injection and purge flow, and associated
coolant injection patterns are presented over a turbine endwall for wide engine …

Non-axisymmetric endwall contouring in axial turbines are becoming popular to improve the
passage aerodynamic performance or the endwall heat transfer characteristics. Meanwhile …

Rising combustor exit temperatures in gas turbine engines necessitate active cooling for the
downstream turbine section to avoid thermal failure. Film-cooling has long been an integral …

The secondary flow vortices make the flow field near the endwall highly three-dimensional.
The jet-to-secondary flow interaction may help to make an efficient film cooling arrangement …

An experimental investigation to obtain detailed film cooling effectiveness distributions on a
cooled turbine blade platform within a linear cascade has been completed. The Reynolds …