Film Cooling Effectiveness for an Advanced-Louver Cooling Scheme for Gas Turbines
Academic Article
Overview
Identity
Additional Document Info
Other
View All
Overview
abstract
A novel film-cooling scheme for high temperature gas turbine applications was introduced in this paper. Compared with the traditional circular hole, the new scheme combines both the advantages of traditional film cooling with those of impingement cooling. The hole that transports coolant fluid from the inside to the outside of the blade is designed in such a way that the coolant must go through a bend before exiting the blade, thus impinging on the blade material. This scheme is expected to produce the greatest coverage on the blade with the least amount of mixing and least possible amount of coolant A benchmark case of a traditional circular hole in a crossflow, the fundamental problem of film cooling, was employed to validate the present methodology with the jet liftoff effect clearly captured in the simulation. Turbulence was modeled using four different turbulence models, namely, k- (including its three variants), k-, Reynolds-stress, and Spalart-Alhnaras with different wall treatments. It was found that the proposed cooling scheme can prevent the jets from penetrating into the mainstream much better and provide more uniform protection on the surface, indicating that the proposed scheme yields superior performance. Copyright 2006 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
