Segmented stator vane

Abstract

A vane assembly may include a vane comprised of a composite material. An outer shroud segment may be disposed at radially outer end of the vane. An inner shroud may define an aperture. A radially inner end of the vane may be disposed within the aperture.

What is claimed is: 
     
         1 . A vane assembly, comprising:
 a vane comprising a composite material;   an outer shroud segment disposed at radially outer end of the vane; and   an inner shroud defining an aperture, wherein a radially inner end of the vane is disposed within the aperture.   
     
     
         2 . The vane assembly of  claim 1 , wherein the outer shroud segment comprises the same composite material as the vane. 
     
     
         3 . The vane assembly of  claim 2 , wherein the outer shroud segment is integrally formed with the vane. 
     
     
         4 . The vane assembly of  claim 1 , wherein the composite material includes at least one of carbon fiber, glass fiber, aramid fiber or para-aramid fiber impregnated with a resin. 
     
     
         5 . The vane assembly of  claim 1 , wherein the vane is cantilever mounted to the inner shroud. 
     
     
         6 . The vane assembly of  claim 5 , further comprising a flexible material disposed within the aperture and between the vane and the inner shroud. 
     
     
         7 . The vane assembly of  claim 6 , further comprising an abradable material formed on an inner diameter surface of the inner shroud. 
     
     
         8 . The vane assembly of  claim 1 , wherein the inner shroud comprises at least one of a composite material or a metal. 
     
     
         9 . A gas turbine engine, comprising:
 an engine section comprising at least one of a compressor section or a fan section, the engine section comprising:
 a vane comprising a composite material, 
 an outer shroud segment disposed at radially outer end of the vane, and 
 an inner shroud defining an aperture, wherein a radially inner end of the vane is disposed within the aperture. 
   
     
     
         10 . The gas turbine engine of  claim 9 , wherein the outer shroud segment comprises the same composite material as the vane. 
     
     
         11 . The gas turbine engine of  claim 10 , wherein the outer shroud segment is integrally formed with the vane. 
     
     
         12 . The gas turbine engine of  claim 9 , wherein the composite material includes at least one of carbon fiber, glass fiber, aramid fiber or para-aramid fiber impregnated with a resin. 
     
     
         13 . The gas turbine engine of  claim 9 , wherein the vane is cantilever mounted to the inner shroud. 
     
     
         14 . The gas turbine engine of  claim 13 , further comprising an engine case structure disposed radially outward from the vane, wherein the vane includes a forward axial flange configured to couple within the engine case structure. 
     
     
         15 . The gas turbine engine of  claim 14 , further comprising a flexible material disposed within the aperture and between the vane and the inner shroud. 
     
     
         16 . The gas turbine engine of  claim 9 , further comprising an abradable material formed on an inner diameter surface of the inner shroud. 
     
     
         17 . A method of manufacturing a vane assembly, comprising:
 forming a vane integrally with an outer shroud segment from a composite material;   disposing a radially inner end of the vane in an aperture defined by an inner shroud;   forming a flexible material within the aperture; and   forming an abradable material over a radially inner surface of the inner shroud.   
     
     
         18 . The method of manufacturing a vane assembly of  claim 17 , further including cantilever mounting the vane to the inner shroud. 
     
     
         19 . The method of manufacturing a vane assembly of  claim 17 , wherein the forming the vane integrally with the outer shroud segment includes injection molding the vane and the outer shroud segment. 
     
     
         20 . The method of manufacturing a vane assembly of  claim 19 , wherein the composite material includes at least one of carbon fiber, glass fiber, aramid fiber or para-aramid fiber impregnated with a resin.