Patent ID: 8366395
Filing Date: 2013-02-05
Classification: F01D,F05D

Abstract:
1. A turbine rotor blade comprising: an airfoil with a leading edge zone, a trailing edge zone, a pressure side zone and a suction side zone; the leading edge zone includes a cooling supply channel connected to a leading edge impingement cavity through a row of metering and impingement holes, and the leading edge impingement cavity is connected to a showerhead arrangement of film cooling holes; the pressure side zone includes a first radial flow cooling supply channel connected to a second radial flow cooling through a row of metering and impingement holes, a first row of film cooling holes connected to the second radial flow cooling channel; the trailing edge zone includes a first radial flow cooling supply channel connected to a second radial flow cooling channel, and a row of exit cooling holes connected to the second radial flow channel and opening onto the trailing edge of the airfoil; the suction side zone includes a plurality of cooling supply channels connected to an impingement cavity through a row of metering and impingement holes, a row of film cooling holes connected to each of the impingement cavities, and the cooling supply channels and impingement cavities being separated from each other such that cooling air does not mix; and, each of the four zones being fluidly separated from each other such that cooling air does not mix.