Locking Assembly For Circumferential Attachments

Abstract

A locking spacer assembly is provided for use with a rotor blade assembly. The locking spacer assembly includes a first end portion, a second end portion, at least one securing device, and a center portion positioned between the first end portion and the second end portion. An opening is defined between the center portion and at least one of the first end portion and the second end portion. The opening is configured to receive the securing device.

1 . A locking spacer assembly for use with a rotor blade assembly, said locking spacer assembly comprising:
 a first end portion;   a second end portion;   at least one securing device; and   a center portion positioned between said first end portion and said second end portion such that an opening is defined between said center portion and at least one of said first end portion and said second end portion, said opening is sized to receive said securing device therein.   
     
     
         2 . A locking spacer assembly in accordance with  claim 1 , wherein said center portion comprises a first side that is configured to engage said first end portion and a second side that is configured to engage said second end portion. 
     
     
         3 . A locking spacer assembly in accordance with  claim 2 , wherein at least one of said first end portion and said second end portion has a first profile, and at least one of said first side and said second side has a second profile that is shaped substantially complementary to the first profile. 
     
     
         4 . A locking spacer assembly in accordance with  claim 3 , wherein one of the first profile and the second profile is a male dovetail profile, and wherein the other of the first profile and the second profile is a female dovetail profile. 
     
     
         5 . A locking spacer assembly in accordance with  claim 1 , wherein said first end portion is substantially similar to said second end portion. 
     
     
         6 . A locking spacer assembly in accordance with  claim 1 , wherein a top of said securing device does not extend beyond a top of at least one of said first end portion, said second end portion ,and said center portion. 
     
     
         7 . A locking spacer assembly in accordance with  claim 1 , wherein said first end portion, said second end portion, and said center portion are configured to carry at least one of a circumferential load and an axial load, and said securing device is configured to carry a radial load. 
     
     
         8 . A rotor blade assembly for use with a turbine engine, said rotor blade assembly comprising:
 a wheel;   a plurality of rotor blades coupled to said wheel; and   a locking spacer assembly coupled to said wheel, said locking spacer assembly comprising a first end portion, a second end portion, at least one securing device, and a center portion positioned between said first end portion and said second end portion such that an opening is defined between said center portion and at least one of said first end portion and said second end portion, said opening is sized to receive said securing device therein.   
     
     
         9 . A rotor blade assembly in accordance with  claim 8 , wherein each of said plurality of blades is substantially similar to another rotor blade. 
     
     
         10 . A rotor blade assembly in accordance with  claim 8 , wherein said locking spacer assembly is positioned between adjacent rotor blades. 
     
     
         11 . A rotor blade assembly in accordance with  claim 8 , wherein said center portion comprises a first side that is configured to engage said first end portion and a second side that is configured to engage said second end portion. 
     
     
         12 . A rotor blade assembly in accordance with  claim 8 , wherein a top of said securing device does not extend beyond a top of at least one of said first end portion, said second end portion ,and said center portion. 
     
     
         13 . A rotor blade assembly in accordance with  claim 8 , wherein said first end portion, said second end portion, and said center portion are configured to carry at least one of a circumferential load and an axial load, and said securing device is configured to carry a radial load. 
     
     
         14 . A turbine engine comprising:
 a rotor; and   a rotor blade assembly comprising a wheel, a plurality of rotor blades coupled to said wheel, and a locking spacer assembly coupled to said wheel, said locking spacer assembly comprising a first end portion, a second end portion, at least one securing device, and a center portion positioned between said first end portion and said second end portion such that an opening is defined between said center portion and at least one of said first end portion and said second end portion, said opening is sized to receive said securing device therein.   
     
     
         15 . A turbine engine in accordance with  claim 14 , wherein each of said plurality of blades is substantially similar to another rotor blade. 
     
     
         16 . A turbine engine in accordance with  claim 14 , wherein said locking spacer assembly is positioned between adjacent rotor blades. 
     
     
         17 . A turbine engine in accordance with  claim 14 , wherein said center portion comprises a first side that is configured to engage said first end portion and a second side that is configured to engage said second end portion. 
     
     
         18 . A turbine engine in accordance with  claim 14 , wherein a top of said securing device does not extend beyond a top of at least one of said first end portion, said second end portion ,and said center portion. 
     
     
         19 . A turbine engine in accordance with  claim 14 , wherein said first end portion, said second end portion, and said center portion are configured to carry at least one of a circumferential load and an axial load, and said securing device is configured to carry a radial load. 
     
     
         20 . A turbine engine in accordance with  claim 14 , wherein said plurality of rotor blades are not directly coupled to said rotor.