Turbine bucket assembly and methods for assembling same

Abstract

A method for assembling a rotor assembly for use with a turbine engine. The method includes providing at least two rotor blades that each include a shank extending between a dovetail and a platform. The shank includes at least one cover plate that extends inwardly from the platform towards the dovetail. An airfoil extends outwardly from the platform. A first rotor blade is coupled to a rotor disk. A second rotor blade is coupled to the rotor disk, such that a cavity is defined between the first and second rotor blades, and such that a seal path is defined between a first rotor blade cover plate and a second rotor blade cover plate.

What is claimed is: 
     
         1 . A method for assembling a rotor assembly for use with a turbine engine, said method comprising:
 providing at least two rotor blades that each include a shank extending between a dovetail and a platform, wherein each shank includes at least one cover plate that extends inwardly from the platform towards the dovetail, and an airfoil that extends outwardly from the platform;   coupling a first rotor blade to a rotor disk;   coupling a second rotor blade to the rotor disk, such that a cavity is defined between the first and second rotor blades, and such that a seal path is defined between a first rotor blade cover plate and a second rotor blade cover plate.   
     
     
         2 . A method in accordance with  claim 1 , further comprising:
 coupling a first sealing assembly to the first rotor blade cover plate; and   coupling a second sealing assembly to the second rotor blade cover plate to form a labyrinth seal path.   
     
     
         3 . A method in accordance with  claim 2 , further comprising:
 coupling a sealing extension to the first rotor blade cover plate to form the first sealing assembly; and   defining a sealing groove within the second rotor blade cover plate.   
     
     
         4 . A method in accordance with  claim 3 , further comprising coupling an abradable surface to an outer surface of the sealing groove. 
     
     
         5 . A method in accordance with  claim 3 , further comprising coupling a plurality of labyrinth teeth to the sealing extension such that a tortuous path is defined between the first sealing assembly and the second sealing assembly. 
     
     
         6 . A method in accordance with  claim 2 , wherein the first sealing assembly extends between the platform and the dovetail. 
     
     
         7 . A rotor blade for a turbine engine, said rotor blade comprising:
 a platform comprising a radially outer surface and a radially inner surface;   an airfoil extending radially outwardly from said platform;   a dovetail adapted to be coupled to a rotor wheel;   a shank extending between said platform and said dovetail, said shank comprising at least one cover plate extending inwardly from said platform towards said dovetail; and   at least one sealing assembly coupled to said cover plate, said sealing assembly extending from said dovetail to said platform, said sealing assembly forms a seal path between said rotor blade and a circumferentially adjacent rotor blade.   
     
     
         8 . A rotor blade in accordance with  claim 7 , wherein said sealing assembly comprises a sealing extension coupled to said cover plate, said sealing extension extending outwardly from said cover plate towards an adjacent rotor blade. 
     
     
         9 . A rotor blade in accordance with  claim 8 , wherein said sealing extension comprises a plurality of labyrinth teeth extending outwardly from said sealing extension, said labyrinth teeth configured to form a tortuous path between said sealing extension and an adjacent rotor blade. 
     
     
         10 . A rotor blade in accordance with  claim 7 , wherein said sealing assembly comprises a recessed sealing groove defined within said cover plate. 
     
     
         11 . A rotor blade in accordance with  claim 10 , wherein said sealing groove comprises an abradable surface extending from an outer surface of said sealing groove. 
     
     
         12 . A rotor blade in accordance with  claim 7 , further comprising a first sealing assembly coupled to said cover plate and an opposite second sealing assembly coupled said cover plate. 
     
     
         13 . A rotor blade in accordance with  claim 12 , wherein said first sealing assembly comprises a sealing extension, said second sealing assembly comprises a recessed groove. 
     
     
         14 . A rotor blade in accordance with  claim 12 , wherein said first sealing assembly and said second sealing assembly each comprise a sealing extension. 
     
     
         15 . A rotor blade in accordance with  claim 12 , wherein said first sealing assembly and said second sealing assembly each comprise a recessed groove. 
     
     
         16 . A gas turbine engine comprising:
 a compressor;   a combustor coupled downstream from said compressor to receive at least some of the air discharged by said compressor;   a rotor shaft coupled to said compressor; and   a plurality of circumferentially-spaced rotor blades coupled to said rotor shaft, each of said plurality of rotor blades comprising:   a platform;   an airfoil extending radially outwardly from said platform;   a dovetail coupled to said rotor shaft;   a shank extending between said platform and said dovetail, said shank comprising at least one cover plate extending inwardly from said platform towards said dovetail; and   at least one sealing assembly coupled to said cover plate such that a seal path is defined between adjacent rotor blades.   
     
     
         17 . A gas turbine engine in accordance with  claim 16 , wherein each of said plurality of rotor blades further comprises a first sealing assembly coupled to said cover plate and an opposite second sealing assembly coupled said cover plate. 
     
     
         18 . A gas turbine engine in accordance with  claim 17 , wherein said first sealing assembly comprises a sealing extension, said second sealing assembly comprises a recessed groove. 
     
     
         19 . A gas turbine engine in accordance with  claim 17 , wherein said first sealing assembly and said second sealing assembly each comprise a sealing extension. 
     
     
         20 . A gas turbine engine in accordance with  claim 17 , wherein said first sealing assembly and said second sealing assembly each comprise a recessed groove.