Turbine blade mid-span shroud assembly

Abstract

A mid-span shroud assembly for a turbine blade includes a pressure side shroud body defining a spar pocket and a fastener hole and a suction side shroud body defining a spar pocket and a fastener hole. The mid-span shroud assembly further includes a spar having a first end portion which extends within the spar pocket of the pressure side shroud body and a second end portion which extends within the spar pocket of the suction side shroud body. The spar is formed to extend through a bore hole of the turbine blade. A fastener is formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body to provide a clamping force to hold the pressure side and suction side shroud bodies against the airfoil.

What is claimed is: 
     
         1 . A mid-span shroud assembly for a turbine blade, the mid-span shroud assembly comprising:
 a pressure side shroud body, the pressure side shroud body defining a spar pocket and a fastener hole;   a suction side shroud body, the suction side shroud body defining a spar pocket and a fastener hole;   a spar having a first end portion extending within the spar pocket of the pressure side shroud body and a second end portion extending within the spar pocket of the suction side shroud body, wherein the spar is formed to extend through a bore hole of the turbine blade; and   a fastener formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body, wherein the fastener provides a clamping force to hold the pressure side shroud body against a pressure side wall of the turbine blade and the suction side shroud body against a suction side wall of the turbine blade.   
     
     
         2 . The mid-span shroud assembly as in  claim 1 , further comprising an interlock feature defined within the spar pocket of the pressure side shroud body. 
     
     
         3 . The mid-span shroud assembly as in  claim 1 , further comprising an interlock feature defined within the spar pocket of the suction side shroud body. 
     
     
         4 . The mid-span shroud assembly as in  claim 1 , wherein at least one of the first and second end portions of the spar includes interlocking features which extend radially outwardly with respect to an axial centerline of the spar. 
     
     
         5 . The mid-span shroud assembly as in  claim 1 , wherein the first end portion of the spar is non-rigidly situated within the spar pocket of the pressure side shroud body. 
     
     
         6 . The mid-span shroud assembly as in  claim 1 , wherein the second end portion of the spar is non-rigidly situated within the spar pocket of the suction side shroud body. 
     
     
         7 . The mid-span shroud assembly as in  claim 1 , wherein the pressure side shroud body includes a mating side portion formed to contour with the pressure side wall of the turbine blade. 
     
     
         8 . The mid-span shroud assembly as in  claim 1 , wherein the suction side shroud includes a mating side portion formed to contour with the suction side wall of the turbine blade. 
     
     
         9 . The mid-span shroud assembly as in  claim 1 , wherein at least a portion of the spar is non-cylindrical. 
     
     
         10 . A turbine blade, comprising:
 an airfoil having a pressure side wall, a suction side wall, a bore hole and a fastener orifice, the bore hole and the fastener orifice extending through the pressure and suction side walls; and   a mid-span shroud assembly, the mid-span shroud assembly comprising:
 a pressure side shroud body having a mating side portion formed to contour to the pressure side wall, the pressure side shroud body defining a spar pocket and a fastener hole; 
 a suction side shroud body having a mating side portion formed to contour to the suction side wall, the suction side shroud body defining a spar pocket and a fastener hole; 
 a spar which extends through the bore hole, the spar including a first end portion and a second end portion, the first end portion situated within the spar pocket of the pressure side shroud body and the second end portion situated within the spar pocket of the suction side shroud body; and 
 a fastener which extends through the fastener hole of the pressure side shroud body, the fastener orifice and the fastener hole of the suction side shroud body, wherein the fastener provides a clamping force to hold the pressure side shroud body and the suction side shroud body against the corresponding pressure side wall and suction side wall. 
   
     
     
         11 . The turbine blade as in  claim 10 , further comprising an interlock feature defined within the spar pocket of the pressure side shroud body. 
     
     
         12 . The turbine blade as in  claim 10 , further comprising an interlock feature defined within the spar pocket of the suction side shroud body. 
     
     
         13 . The turbine blade as in  claim 10 , wherein at least one of the first and second end portions of the spar includes interlocking features which extend radially outwardly with respect to an axial centerline of the spar. 
     
     
         14 . The turbine blade as in  claim 10 , wherein the first end portion of the spar is non-rigidly situated within the spar pocket of the pressure side shroud body. 
     
     
         15 . The turbine blade as in  claim 10 , wherein the second end portion of the spar is non-rigidly situated within the spar pocket of the suction side shroud body. 
     
     
         16 . The turbine blade as in  claim 10 , wherein the spar includes an intermediate portion which extends between the first and second end portions and extends through the bore hole, wherein the intermediate portion of the spar and the bore hole are non-cylindrical. 
     
     
         17 . A gas turbine, comprising:
 a compressor section;   a combustor section; and   a turbine section, the turbine section including a plurality of turbine blades coupled to a rotor shaft, each turbine blade including an airfoil having a pressure side wall, a suction side wall, a bore hole and a fastener orifice, the bore hole and the fastener orifice extending through the pressure and suction side walls, each turbine blade including a mid-span shroud assembly coupled to the turbine blade, the mid-span shroud assembly comprising:
 a pressure side shroud body having a mating side portion formed to contour to the pressure side wall, the pressure side shroud body defining a spar pocket and a fastener hole; 
 a suction side shroud body having a mating side portion formed to contour to the suction side wall, the suction side shroud body defining a spar pocket and a fastener hole; 
 a spar which extends through the bore hole, the spar including a first end portion and a second end portion, the first end portion extending within the spar pocket of the pressure side shroud body and the second end portion extending within the spar pocket of the suction side shroud body; and 
 a fastener which extends through the fastener hole of the pressure side shroud body, the fastener orifice and the fastener hole of the suction side shroud body, wherein the fastener provides a clamping force to hold the pressure side shroud body and the suction side shroud body against the corresponding pressure side wall and suction side wall. 
   
     
     
         18 . The gas turbine as in  claim 17 , wherein the pressure side shroud body includes an interlock feature defined within the pressure side shroud body spar pocket and the suction side shroud body includes an interlock feature defined within the suction side shroud body spar pocket. 
     
     
         19 . The gas turbine as in  claim 17 , wherein at least one of the first and second end portions of the spar includes interlocking members which extend radially outwardly with respect to an axial centerline of the spar. 
     
     
         20 . The gas turbine as in  claim 17 , wherein the first end portion of the spar is non-rigidly situated within the spar pocket of the pressure side shroud body, and wherein the second end portion of the spar is non-rigidly situated within the spar pocket of the suction side shroud body.