Methods and apparatus for assembling gas turbine engines

Abstract

A method for assembling a gas turbine engine compressor having a plurality of stages and a plurality of blades coupled to each respective stage includes depositing a silicone oxime sealant onto at least a portion of a compressor blade, and coupling the compressor blade to a compressor disk such that the silicone oxime sealant is between the compressor blade and the compressor disk.

1 . A method for assembling a gas turbine engine compressor having a plurality of disks and a plurality of blades coupled to each respective disk, said method comprising: 
 depositing a silicone oxime sealant onto at least a portion of a compressor blade or a portion of a respective disk; and    coupling the compressor blade to a compressor disk such that the silicone oxime sealant is between the compressor blade and the compressor disk.    
   
   
       2 . A method in accordance with  claim 1  wherein depositing a silicone oxime sealant further comprises depositing a room temperature vulcanizing silicone oxime sealant onto at least a portion of the compressor blade or the respective disk.  
   
   
       3 . A method in accordance with  claim 1  wherein coupling the compressor blade to a compressor disk further comprises coupling the compressor blade to at least one of a first stage compressor disk, a second stage compressor disk, and a third stage compressor disk.  
   
   
       4 . A method in accordance with  claim 1  wherein depositing a silicone oxime sealant further comprises depositing a silicone oxime sealant that is operable at a temperature greater than 600 degrees Fahrenheit onto at least a portion of the compressor blade or the disk.  
   
   
       5 . A method in accordance with  claim 1  further comprising: 
 depositing a silicone oxime sealant onto at least a portion of a plurality of compressor blades; and    coupling the plurality of compressor blades to the compressor disk.    
   
   
       6 . A method in accordance with  claim 1  wherein depositing a silicone oxime sealant further comprises depositing a silicone oxime sealant onto at least a portion of a compressor blade dovetail.  
   
   
       7 . A method in accordance with  claim 1  further comprising coupling the compressor blade to the compressor disk after the silicone oxime sealant has substantially cured.  
   
   
       8 . A gas turbine engine rotor assembly comprising: 
 a rotor disk;    a plurality of circumferentially-space rotor blades coupled to said rotor disk; and    a silicone oxime sealant deposited onto at least a portion of said rotor blade or said rotor disk such that said silicone oxime sealant is between said rotor blade and said disk.    
   
   
       9 . A gas turbine engine rotor assembly in accordance with  claim 8  wherein said rotor disk comprises a compressor rotor disk, and said rotor blades comprise compressor rotor blades.  
   
   
       10 . A gas turbine engine rotor assembly in accordance with  claim 8  wherein said silicone oxime sealant comprises a room temperature vulcanizing silicone oxime sealant.  
   
   
       11 . A gas turbine engine rotor assembly in accordance with  claim 8  wherein said rotor disk comprises at least one of a first stage compressor rotor disk, a second stage compressor rotor disk, and a third stage compressor rotor disk.  
   
   
       12 . A gas turbine engine rotor assembly in accordance with  claim 8  wherein said silicone oxime sealant is operable at a temperature greater than 600 degrees Fahrenheit.  
   
   
       13 . A gas turbine engine rotor assembly in accordance with  claim 8  wherein said rotor blade comprises a dovetail, said turbine rotor disk comprises a dovetail slot, said silicone oxime sealant deposited between said dovetail and said dovetail slot.  
   
   
       14 . A gas turbine engine comprising: 
 a rotor disk;    a plurality of rotor blades coupled to said rotor disk; and    a silicone oxime sealant deposited onto at least a portion of at least one of said rotor blades or said rotor disk such that said silicone oxime sealant is between said rotor blade and said disk.    
   
   
       15 . A gas turbine engine in accordance with  claim 14  wherein said rotor disk comprises a compressor rotor disk, and said rotor blades comprise compressor rotor blades.  
   
   
       16 . A gas turbine engine in accordance with  claim 14  wherein said silicone oxime sealant comprises a room temperature vulcanizing silicone oxime sealant.  
   
   
       17 . A gas turbine engine in accordance with  claim 14  wherein said rotor disk comprises at least one of a first stage compressor rotor disk, a second stage compressor rotor disk, and a third stage compressor rotor disk.  
   
   
       18 . A gas turbine engine in accordance with  claim 14  wherein said silicone oxime sealant is operable at a temperature greater than 600 degrees Fahrenheit.  
   
   
       19 . A gas turbine engine in accordance with  claim 14  wherein said rotor blade comprises a dovetail, said turbine rotor disk comprises a dovetail slot, said silicone oxime sealant deposited between said dovetail and said dovetail slot.