Chevron platform turbine vane

Abstract

Gas turbine vanes of a gas turbine vane assembly have a reconfigured platform shape so as to reduce the ingestion of hot combustion gases into platform gaps between adjacent vane assemblies is disclosed. The vane platforms are configured so the joint between adjacent vanes is repositioned a sufficient distance away from the leading edge of the vane airfoil and the associated bow wave generated by the hot combustion gases passing over the airfoil leading edge.

1 . A gas turbine vane comprising:
 an inner arc-shaped platform having a pressure side radial face and a suction side radial face where the pressure side radial face comprises a first portion, a second portion, and a relief cut at the intersection of the first portion and the second portion;   an outer arc-shaped platform spaced a distance radially outward of the inner arc-shaped platform and having a pressure side radial face and a suction side radial face where the pressure side radial face comprises a first portion, a second portion, and a relief cut at the intersection of the first portion and the second portion; and,   at least one airfoil extending between the inner arc-shaped platform and the outer arc-shaped platform.   
     
     
         2 . The gas turbine vane of  claim 1 , wherein the first portion of the inner arc-shaped platform is generally co-planar with the first portion of the outer arc-shaped platform and the second portion of the inner arc-shaped platform is generally co-planar with the second portion of the outer arc-shaped platform. 
     
     
         3 . The gas turbine vane of  claim 1 , wherein the first portion and the second portion of the pressure side radial face of the inner arc-shaped platform further comprises an inner seal slot. 
     
     
         4 . The gas turbine vane of  claim 1 , wherein the first portion and the second portion of the pressure side radial face of the outer arc-shaped platform further comprises an outer seal slot. 
     
     
         5 . The gas turbine vane of  claim 1  further comprising a bond coating and a thermal barrier coating applied to a portion of the inner arc-shaped platform, a portion of the outer arc-shaped platform, and the at least one airfoil. 
     
     
         6 . The gas turbine vane of  claim 1 , wherein the airfoil is air cooled by a source of air entering the airfoil through the outer arc-shaped platform. 
     
     
         7 . The gas turbine vane of  claim 1 , wherein the inner arc-shaped platform, the outer arc-shaped platform, and the airfoil are integrally cast. 
     
     
         8 . A gas turbine vane comprising:
 an inner arc-shaped platform having a pressure side radial face and a suction side radial face where the suction side radial face comprises a first portion and a second portion;   an outer arc-shaped platform spaced a distance radially outward of the inner arc-shaped platform and having a pressure side radial face and a suction side radial face where the suction side radial face comprises a first portion and a second portion; and,   at least one airfoil extending between the inner arc-shaped platform and the outer arc-shaped platform;   
     
     
         9 . The gas turbine vane of  claim 8 , wherein the first portion of the inner arc-shaped platform is generally co-planar with the first portion of the outer arc-shaped platform and the second portion of the inner arc-shaped platform is generally co-planar with the second portion of the outer arc-shaped platform. 
     
     
         10 . The gas turbine vane of  claim 8 , wherein the first portion and the second portion of the suction side radial face of the inner arc-shaped platform further comprise a seal slot. 
     
     
         11 . The gas turbine vane of  claim 8 , wherein the first portion and the second portion of the suction side radial face of the outer arc-shaped platform further comprise a seal slot. 
     
     
         12 . The gas turbine vane of  claim 8  further comprising a bond coating and a thermal barrier coating applied to a portion of the inner arc-shaped platform, a portion of the outer arc-shaped platform, and the at least one airfoil. 
     
     
         13 . The gas turbine vane of  claim 8 , wherein the airfoil is air cooled by a source of air entering the airfoil through the outer arc-shaped platform. 
     
     
         14 . The gas turbine vane of  claim 8 , wherein the inner arc-shaped platform, the outer arc-shaped platform, and the airfoil are integrally cast. 
     
     
         15 . A gas turbine vane assembly comprising:
 a first vane assembly having:
 a first inner platform having a pressure side radial face and a suction side radial face, where the pressure side radial face has a first portion, a second portion, and a relief cut at the intersection of the first and second portion; 
 a first outer platform spaced a radial distance from the first inner platform and having a pressure side radial face and a suction side radial face, where the pressure side radial face has a first portion and a second portion, and a relief cut at the intersection of the first and second portion; and, 
 a first airfoil extending between the first inner platform and first outer platform; 
   a second vane assembly having:
 a second inner platform having a pressure side radial face and a suction side radial face, where the suction side radial face has a first portion and a second portion; 
 a second outer platform spaced a radial distance from the second inner platform and having a pressure side radial face and a suction side radial face, where the suction side radial face has a first portion and a second portion; and, 
 a second airfoil extending between the second inner platform and second outer platform; and, 
   a fastener mechanism positioned adjacent the first and second outer platforms and the first and second inner platforms for securing the first vane assembly to the second vane assembly.   
     
     
         16 . The gas turbine vane assembly of  claim 15 , wherein the fastener mechanism comprises a first bracket secured to the first vane assembly and a second bracket secured to the second vane assembly and one or more removable fasteners. 
     
     
         17 . The gas turbine vane assembly of  claim 16 , wherein the suction side radial face of the outer platform of the first vane assembly is secured to the pressure side radial face of the outer platform of the second vane assembly by the fastener mechanism. 
     
     
         18 . The gas turbine vane assembly of  claim 17 , wherein the fastener mechanism causes the first vane assembly to contact the second vane assembly so as to form a sealed interface. 
     
     
         19 . The gas turbine vane assembly of  claim 17 , wherein the first portion of the inner arc-shaped platform is generally co-planar with the first portion of the outer arc-shaped platform and the second portion of the inner arc-shaped platform is generally co-planar with the second portion of the outer arc-shaped platform. 
     
     
         20 . The gas turbine vane assembly of  claim 15  further comprising a plurality of flexible sheet metal seals positioned in respective slots of the inner and outer platforms to provide a seal between adjacent turbine vane assemblies.