Patent ID: 8870524
Filing Date: 2014-10-28
Classification: B22C,F01D,F05D

Abstract:
1. A turbine stator vane for an industrial gas turbine engine, the vane comprising: an airfoil extending between an outer diameter endwall and an inner diameter endwall; a three-pass serpentine flow cooling circuit with a first leg located along a leading edge of the airfoil and a third leg located adjacent to a trailing edge of the airfoil; an inner diameter turn channel located below the inner diameter endwall and connected between the first leg and a second leg of the serpentine flow circuit; an outer diameter turn channel located above the outer diameter endwall and connected between the second leg and the third leg of the serpentine flow circuit; a row of exit cooling holes located along a trailing edge of the airfoil and connected to the third leg; a purge air hole connected to an end of the third leg; two purge air holes formed in the inner endwall turn channel and covered with an inner diameter turn channel cover plate; and, two purge air holes formed in the outer endwall turn channel and covered with an outer diameter turn channel cover plate.