Abstract
In order to generate large electrical power of gas turbine, the turbine inlet temperature has been increased. The hot components of gas turbine were exposed to high thermal load and it needed a proper cooling system. The film cooling has been widely used to protect the hot components of gas turbine from combustion gas. Many film cooling holes were placed in the airfoil and it was designed the coolant flow smoothly from the internal cavity to the external surface. Therefore, the direction of coolant injection and the flow development length are important factors as film cooling holes design. This study investigates the film cooling effectiveness and flow characteristics of forward and backward injection film cooling holes according to the change in the flow development length and blowing ratio. The backward injection film cooling shows a complicated flow characteristics and high film cooling effectiveness on the horizontal plane compared with the forward injection film cooling case.
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