Stator vane platform with flanges

Abstract

Disclosed is a gas turbine engine that includes a plurality of stator vanes. Each of the stator vanes includes an airfoil section and a platform provided at an end of the airfoil section. The platforms are provided with flanges on opposed ends thereof, and the flanges are fastened to corresponding flanges of an adjacent one of the plurality of stator vanes.

What is claimed is: 
     
         1 . A gas turbine engine, comprising:
 a plurality of stator vanes, each of the plurality of stator vanes including an airfoil section and a platform provided at an end of the airfoil section, the platform provided with flanges on opposed ends thereof, the flanges being fastened to corresponding flanges of an adjacent one of the plurality of stator vanes.   
     
     
         2 . The gas turbine engine as recited in  claim 1 , wherein the flanges are provided on circumferential ends of the platform. 
     
     
         3 . The gas turbine engine as recited in  claim 2 , wherein a length dimension of the flanges is provided in a direction generally parallel to an engine central longitudinal axis. 
     
     
         4 . The gas turbine engine as recited in  claim 3 , wherein the flanges include inner and outer faces generally perpendicular the platform. 
     
     
         5 . The gas turbine engine as recited in  claim 4 , wherein the flanges are fastened to one another such that the outer faces of the flanges directly abut one another. 
     
     
         6 . The gas turbine engine as recited in  claim 5 , wherein the flanges include openings configured to receive fasteners. 
     
     
         7 . The gas turbine engine as recited in  claim 6 , wherein the fasteners include at least one of bolts, pins, and springs. 
     
     
         8 . The gas turbine engine as recited in  claim 6 , wherein the fasteners fasten adjacent flanges to one another. 
     
     
         9 . The gas turbine engine as recited in  claim 6 , wherein the fasteners fasten the flanges to a static structure of the gas turbine engine via a respective coupling. 
     
     
         10 . The gas turbine engine as recited in  claim 6 , including at least one resilient member connected to the flange and to the platform to reduce bending of the flange. 
     
     
         11 . The gas turbine engine as recited in  claim 1 , wherein at least one of the plurality of stator vanes is made of a ceramic matrix composite (CMC) material. 
     
     
         12 . The gas turbine engine as recited in  claim 1 , further including a compressor section, a combustor section, and a turbine section, the turbine section including a stationary stage, the stator vanes provided in the stationary stage. 
     
     
         13 . The gas turbine engine as recited in  claim 1 , wherein each of the plurality of stator vanes includes a first platform at a radially outer end of the airfoil section, and a second platform at a radially inner end of the airfoil section, each of the first and second platforms provided with flanges on opposed ends thereof, wherein the flanges associated with the first platform are fastened to flanges of a first platform of an adjacent stator vane, and the flanges associated with the second platform are not fastened to the flanges of an adjacent stator vane to allow the second platform to be radially free. 
     
     
         14 . A stator vane for a gas turbine engine, comprising:
 an airfoil section;   a platform provided at an end of the airfoil section, the platform having a fore end, an aft end, and circumferential ends, the platform including flanges provided on the circumferential ends, the flanges configured to abut flanges of a similar stator vane.   
     
     
         15 . The stator vane as recited in  claim 14 , wherein the airfoil section is provided generally along a radial direction. 
     
     
         16 . The stator vane as recited in  claim 15 , wherein the flanges are provided such that a length thereof is generally perpendicular to the radial direction. 
     
     
         17 . The stator vane as recited in  claim 14 , wherein each flange includes at least one opening for receiving a fastener. 
     
     
         18 . The stator vane as recited in  claim 14 , wherein the stator vane is a singlet. 
     
     
         19 . The stator vane as recited in  claim 14 , wherein at least a portion of the stator vane is made of ceramic matrix composite (CMC) material. 
     
     
         20 . The stator vane as recited in  claim 14 , wherein the flanges are integrally formed with the stator vane.