Gas turbine blade and manufacturing method
Abstract:
A blade for a gas turbine is described, the blade comprising a trailing edge and a trailing edge cooling channel extending from a first upstream end to a second downstream end, in which the width of the trailing edge cooling channel in the direction perpendicular to the camber line of the blade varies and the narrowest width in the trailing edge cooling channel is at the first upstream end, so as to provide a blade where the trailing edge can be removed with a minimal change or no change in the cooling flow capacity through the trailing edge cooling channel. Related methods are also described.
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