Rotor assembly for use in gas turbine engines and method for assembling the same

Abstract

A method of assembling a rotor assembly for use with a turbine engine. The method includes providing a rotor shaft and coupling at least one rotor disk to the rotor shaft such that a cooling path is defined between the rotor shaft and the rotor disk. The rotor disk includes a substantially cylindrical body that has upstream and downstream surfaces extending between a radially inner edge and a radially outer edge. A first cooling plate is coupled to the downstream surface of the rotor disk to define a cooling duct between the first cooling plate and the downstream surface. The cooling duct is configured to channel a cooling fluid from the cooling path to the towards the outer edge.

1 . A method of assembling a rotor assembly for use with a turbine engine, said method comprising:
 providing a rotor shaft;   coupling at least one rotor disk to the rotor shaft such that a cooling path is defined between the rotor shaft and the at least one rotor disk, the at least one rotor disk including a substantially cylindrical body having upstream and downstream surfaces extending between a radially inner edge and a radially outer edge; and   coupling a first cooling plate to the downstream surface of the at least one rotor disk to define a cooling duct between the first cooling plate and the downstream surface, the cooling duct configured to channel a cooling fluid from the cooling path to the towards the outer edge.   
     
     
         2 . A method in accordance with  claim 1 , further comprising coupling a plurality of vanes between the downstream surface and the first cooling plate, each vane extends outwardly from the inner edge towards the outer edge, adjacent vanes are spaced a circumferential distance apart such that a cooling channel is defined between each pair of circumferentially-spaced vanes. 
     
     
         3 . A method in accordance with  claim 1 , wherein coupling a plurality of vanes further comprises:
 providing each vane having an arcuate outer surface shaped to channel fluid through each cooling channel; and   coupling each vane between the downstream surface and the first cooling plate.   
     
     
         4 . A method in accordance with  claim 1 , further comprises coupling an inner flange to the first cooling plate, the inner flange extending inwardly from the first cooling plate towards the rotor shaft. 
     
     
         5 . A method in accordance with  claim 1 , further comprising coupling a second cooling plate to the upstream surface of the at least one rotor disk such that a return air duct is defined between the second cooling plate and the upstream surface. 
     
     
         6 . A method in accordance with  claim 5 , further comprising coupling a first rotor disk to an adjacent second rotor disk such that the first rotor disk cooling duct is in flow communication with the second rotor disk return air duct. 
     
     
         7 . A rotor assembly for use with a turbine, said rotor assembly comprising:
 a rotor shaft;   at least one rotor disk coupled to said rotor shaft such that a cooling path is defined between said rotor shaft and said at least one rotor disk, said at least one rotor disk comprises a substantially cylindrical body extending between a radially inner edge and a radially outer edge, said body extending generally axially between an upstream surface and a downstream surface; and   a cooling assembly coupled to said at least one rotor disk, said cooling assembly comprising a first cooling plate coupled to said downstream surface such that a cooling duct is defined between said first cooling plate and said downstream surface, said cooling duct configured to channel cooling fluid from the cooling path towards said outer edge.   
     
     
         8 . A rotor assembly in accordance with  claim 7 , wherein said cooling assembly further comprises a plurality of vanes coupled between said downstream surface and said first cooling plate, each said vane extends outwardly from said inner edge towards said outer edge, adjacent said vanes are spaced a circumferential distance apart such that a cooling channel is defined between each said pair of circumferentially-adjacent vanes. 
     
     
         9 . A rotor assembly in accordance with  claim 8 , wherein each said vane comprises an arcuate outer surface shaped to channel cooling fluid through each said cooling channel. 
     
     
         10 . A rotor assembly in accordance with  claim 8 , wherein each said pair of circumferentially-spaced vanes are spaced such that said cooling channel is defined with an inlet opening that is smaller than an outlet opening. 
     
     
         11 . A rotor assembly in accordance with  claim 8 , wherein said first cooling plate comprises an inner flange that extends inwardly from said first cooling plate to define an inlet opening that extends into a cooling fluid path defined between said rotor disk inner edge and said shaft. 
     
     
         12 . A rotor assembly in accordance with  claim 8 , wherein said cooling assembly further comprises a second cooling plate coupled to said upstream surface such that a return air duct is defined between said second cooling plate and said upstream surface. 
     
     
         13 . A rotor assembly in accordance with  claim 12 , wherein said at least one rotor disk comprises at least a first rotor disk coupled to a second rotor disk, said first cooling plate is coupled to adjacent second cooling plate such that said cooling duct is coupled in flow communication with said return air duct. 
     
     
         14 . A rotor assembly in accordance with  claim 7 , wherein said cooling assembly further comprises at least one turbulator coupled to said first cooling plate. 
     
     
         15 . A turbine engine comprising:
 a compressor;   a turbine coupled in flow communication with said compressor to receive at least some of the air discharged by said compressor;   a rotor shaft rotatably coupled to said turbine;   at least one rotor disk coupled to said rotor shaft such that a cooling path is defined between said rotor shaft and said at least one rotor disk, said at least one rotor disk comprises a substantially cylindrical body extending between a radially inner edge and a radially outer edge, said body extending generally axially between an upstream surface and a downstream surface; and   a cooling assembly coupled to said at least one rotor disk, said cooling assembly comprising a first cooling plate coupled to said downstream surface such that a cooling duct is defined between said first cooling plate and said downstream surface, said cooling duct configured to channel cooling fluid from the cooling path towards said outer edge.   
     
     
         16 . A turbine engine in accordance with  claim 15 , wherein said cooling assembly further comprises a plurality of vanes coupled between said downstream surface and said first cooling plate, each said vane extends outwardly from said inner edge towards said outer edge, adjacent said vanes are spaced a circumferential distance apart such that a cooling channel is defined between each said pair of circumferentially-adjacent vanes. 
     
     
         17 . A turbine engine in accordance with  claim 16 , wherein each said vane comprises an arcuate outer surface shaped to channel cooling fluid through each said cooling channel. 
     
     
         18 . A turbine engine in accordance with  claim 15 , wherein said first cooling plate comprises an inner flange that extends inwardly from said first cooling plate to define an inlet opening that extends into a cooling fluid path defined between said rotor disk inner edge and said shaft. 
     
     
         19 . A turbine engine in accordance with  claim 15 , wherein said cooling assembly further comprises a second cooling plate coupled to said upstream surface such that a return air duct is defined between said second cooling plate and said upstream surface. 
     
     
         20 . A turbine engine in accordance with  claim 19 , wherein said at least one rotor disk comprises a first rotor disk coupled to a second rotor disk, said first cooling plate is coupled to adjacent second cooling plate such that said cooling duct is coupled in flow communication with said return air duct.