Manufacture of full ring strut vane pack

Abstract

A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform. An outer wrap is disposed about an outer periphery of the annular ring and over an interface between outer platforms of adjacent ones of the plurality of vane segments.

What is claimed is: 
     
         1 . A vane assembly for a gas turbine engine comprising:
 a plurality of individual vane segments forming an annular ring with each of the plurality of vane segments formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform; and   an wrap disposed about one of an outer periphery and an inner periphery of the annular ring and over an interface between a corresponding inner and outer platform of adjacent ones of the plurality of vane segments.   
     
     
         2 . The vane assembly as recited in  claim 1 , wherein the wrap comprises an outer wrap disposed about the outer periphery and covering the interface between outer platforms of adjacent ones of the plurality of vane segments. 
     
     
         3 . The vane assembly as recited in  claim 1 , wherein the wrap comprises an inner wrap disposed about an inner periphery of the annular ring over an interface between inner platforms of adjacent ones of the plurality of vane segments. 
     
     
         4 . The vane assembly as recited in  claim 1 , wherein the wrap comprise a ceramic matrix composite material. 
     
     
         5 . The vane assembly as recited in  claim 1 , wherein the wrap includes a silicon carbide monofilament. 
     
     
         6 . The vane assembly as recited in  claim 1 , wherein the wrap comprises a plurality of plies applied to the plurality of vane segments. 
     
     
         7 . The vane assembly as recited in  claim 1 , wherein each of the plurality of vane segments include a cavity extending through the outer platform, airfoils and inner platform. 
     
     
         8 . The vane assembly as recited in  claim 1 , wherein the plurality of vane segments are at least partially cured prior to installation of the wrap. 
     
     
         9 . A mid-turbine frame for a gas turbine engine comprising:
 a plurality of individual vane segments forming an annular ring with each of the plurality of vane segments formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform;   an outer wrap disposed about an outer periphery of the annular ring over an interface between outer platforms of adjacent ones of the plurality of vane segments; and   a support tie-rod extending through at least one of the plurality of vane segments and attached at a first end to an outer case structure and on a second end to an inner case structure.   
     
     
         10 . The mid-turbine frame as recited in  claim 9 , including an inner wrap disposed about an inner periphery of the annular ring over an interface between inner platforms of adjacent ones of the plurality of vane segments. 
     
     
         11 . The vane assembly as recited in  claim 10 , wherein the outer wrap and the inner wrap comprise a ceramic matrix composite material. 
     
     
         12 . The vane assembly as recited in  claim 11 , wherein at least one of the outer wrap and inner wrap includes a silicon carbide monofilament. 
     
     
         13 . The vane assembly as recited in  claim 10 , wherein at least one of the outer wrap and inner wrap comprise a plurality of plies applied to the plurality of vane segments. 
     
     
         14 . A method of assembling a full ring vane pack comprising:
 forming a plurality of vane segments from a ceramic matrix composite material including at least one airfoils extending between an outer platform and an inner platform;   assembling an annular ring with the plurality of vane segments by abutting corresponding outer platforms and inner platforms; and   wrapping an outer periphery of the annular ring with a ceramic matrix composite material over an interface between outer platforms of adjacent ones of the plurality of vane segments.   
     
     
         15 . The method as recited in  claim 14 , including wrapping an inner periphery of the annular ring with a ceramic matrix composite material over an interface between inner platforms of adjacent ones of the plurality of vane segments. 
     
     
         16 . The method as recited in  claim 14 , including curing the wrapped ceramic matrix composite material around the plurality of vane segments. 
     
     
         17 . The method as recited in  claim 14 , wherein each of the plurality of vane segments are fully cured prior to assembly into the annular ring. 
     
     
         18 . The method as recited in  claim 14 , wherein each of the plurality of vane segments are not fully cured when assembled into the annular ring and both the outer ceramic matrix composite wrapping and plurality of vane segments are finish cured together.