Turbine engine vane arrangement having a plurality of interconnected vane arrangement segments

Abstract

A turbine engine vane arrangement and a method for manufacturing a turbine engine vane arrangement are provided. The vane arrangement includes a plurality of vane arrangement segments arranged circumferentially around an axial centerline. Each of the vane arrangement segments includes an airfoil that extends radially between a first platform segment and a second platform segment. The first platform segment extends circumferentially between a first mate face and a second mate face. The first mate face of a first of the vane arrangement segments is bonded to the second mate face of a second of the vane arrangement segments.

What is claimed is: 
     
         1 . A turbine engine vane arrangement, comprising:
 a plurality of vane arrangement segments arranged circumferentially around an axial centerline, the vane arrangement segments consisting of a plurality of base segments and a keystone segment;   the base segments and the keystone segment each comprising an airfoil extending radially between a first platform segment and a second platform segment;   the first platform segment extending circumferentially between a first mate face and a second mate face;   the first mate face of a first of the base segments bonded to the second mate face of the keystone segment; and   the first platform segment comprising a width that extends circumferentially between the first mate face and the second mate face, the width of each of the base segments having a first value, and the width of the keystone segment having a second value that is different than the first value.   
     
     
         2 . The vane arrangement of  claim 1 , wherein the first mate face of the first of the base segments is brazed to the second mate face of the keystone segment. 
     
     
         3 . The vane arrangement of  claim 1 , wherein the first platform segment is configured as a radial inner platform segment, and the second platform segment is configured as a radial outer platform segment. 
     
     
         4 . The vane arrangement of  claim 1 , wherein the first platform segment is configured as a radial outer platform segment, and the second platform segment is configured as a radial inner platform segment. 
     
     
         5 . The vane arrangement of  claim 1 , wherein
 the second platform segment extends circumferentially between a first mate face and a second mate face; and   the first mate face of the second platform segment of the first of the base segments is bonded to the second mate face of the second platform segment of the keystone segment.   
     
     
         6 . The vane arrangement of  claim 1 , wherein the airfoil, the first platform segment and the second platform segment of one of the base segments are integral to one another. 
     
     
         7 . The vane arrangement of  claim 1 , wherein one of the base segments further comprises a second airfoil that extends radially between the respective first platform segment and the respective second platform segment. 
     
     
         8 . The vane arrangement of  claim 1 , wherein the vane arrangement segments are configured as turbine section vane arrangement segments. 
     
     
         9 . The vane arrangement of  claim 1 , further comprising:
 an outer platform formed by the vane arrangement segments; and   an annular band circumscribing the outer platform, wherein the band is bonded to the outer platform.   
     
     
         10 . The vane arrangement of  claim 1 , wherein one of the vane arrangement segments is cast as a unitary body. 
     
     
         11 . The vane arrangement of  claim 10 , wherein the airfoil comprises a hollow airfoil. 
     
     
         12 . The vane arrangement of  claim 1 , further comprising:
 an inner platform formed by the vane arrangement segments; and   an annular band arranged radially within vane arrangement segments such that the inner platform circumscribes the band, wherein the band is bonded to the inner platform.