Patent attributes
A turbine blade with a film cooling holes arrangement to supply film cooling to hot sections on the pressure side and suction side of the blade. The cooling flow circuit for the blade uses a serpentine flow cooling path to supply cooling air to a number of impingement cavities, the impingement cavities being connected to film cooling holes to discharge film cooling air to key spots on the pressure side wall and suction side wall of the blade that require film cooling air. The serpentine flow cooling channels are located on the opposite side of the blade from the impingement cavity in which the channel communicates with through metering and impingement holes. The first and second legs of the serpentine flow cooling channels are located on the pressure side, and the third leg or channel is located on the suction side of the blade downstream from the gage point and where no further film cooling is preferred. By moving the serpentine flow cooling supply channel from the pressure side to the suction side in the third leg, the film cooling holes on the pressure side of the blade can be supplied through metering holes and an impingement cavity that discharge the film cooling air. The remaining legs of the serpentine flow cooling supply channels are in the trailing edge region of the blade, and a plurality of exit holes discharge cooling air from the last leg of the cooling supply channels.
