Dual bayonet engagement and method of assembling a combustor liner in a gas turbine engine

Abstract

A combustor assembly is provided that includes a forward annular liner, an aft annular liner, and a stator. The forward annular liner has an inner annular edge and an outer annular edge. The aft annular liner is spaced apart from the forward annular liner to form a combustion chamber. The aft annular liner has an inner annular edge and an outer annular edge. The stator has a forward end and an aft end. The stator forward end includes an inner annular edge and an outer annular edge. The stator forward end inner annular edge is coupled to the aft annular liner outer annular edge via a first bayonet mount system, and the stator forward end outer annular edge is coupled to the forward annular liner outer annular edge via a second bayonet mount system.

1 . A combustor assembly comprising: 
 a forward annular liner having an inner annular edge and an outer annular edge;    an aft annular liner spaced apart from the forward annular liner to form a combustion chamber, the aft annular liner having an inner annular edge and an outer annular edge; and    a stator having a forward end including an inner annular edge and an outer annular edge, the stator forward end inner annular edge coupled to the aft annular liner outer annular edge via a first bayonet mount system, and the stator forward end outer annular edge coupled to the forward annular liner outer annular edge via a second bayonet mount system.    
   
   
       2 . The assembly of  claim 1 , wherein the first bayonet mount system includes a first and a second bayonet engagement face, the first bayonet engagement face formed on the aft annular liner outer annular edge and the second bayonet engagement face formed on the stator forward end inner annular edge.  
   
   
       3 . The assembly of  claim 2 , wherein the second bayonet mount system includes a first and a second bayonet engagement face, the first bayonet engagement face formed on the forward annular liner outer annular edge and the second bayonet engagement face formed on the stator forward end outer annular edge.  
   
   
       4 . The assembly of  claim 1 , wherein the aft annular liner inner annular edge is proximate to the forward annular liner inner annular edge and the system further comprises: 
 an annular gap formed between the aft annular liner and the forward annular liner.    
   
   
       5 . The assembly of  claim 4 , further comprising a slinger coupled to the shaft, the slinger including a plurality of holes formed therein that communicate with the annular gap.  
   
   
       6 . The assembly of  claim 1 , wherein the stator includes an aft end, the aft annular liner assembly further comprises a labyrinth seal component extending axially relative to the shaft including a forward end and an aft end, and the labyrinth seal component forward end coupled to the aft annular liner inner annular edge and the labyrinth seal aft end coupled to the stator aft end.  
   
   
       7 . The assembly of  claim 6 , wherein the labyrinth seal component includes a first and a second labyrinth seal coupled thereto.  
   
   
       8 . The assembly of  claim 6 , further comprising a flow discourager coupled to the labyrinth seal aft end.  
   
   
       9 . A combustor assembly kit for implementation into a combustor system, comprising: 
 a forward annular liner having an inner annular edge and an outer annular edge;    an aft annular liner configured to be spaced apart from the forward annular liner to form a combustion chamber, the aft annular liner having an inner annular edge and an outer annular edge; and    a stator having a forward end including an inner annular edge and an outer annular edge, the stator forward end inner annular edge configured to be coupled to the aft annular liner outer annular edge via a first bayonet mount system, and the stator forward end outer annular edge configured to be coupled to the forward annular liner outer annular edge via a second bayonet mount system.    
   
   
       10 . The kit of  claim 9 , wherein the stator includes an aft end and the kit further comprises a labyrinth seal component configured to extend axially along and to be disposed about a shaft, the labyrinth seal component including a forward end and an aft end, the labyrinth seal component forward end configured to couple to the aft annular liner inner annular edge and the labyrinth seal component aft end configured to couple to the stator aft end.  
   
   
       11 . The kit of  claim 10 , further comprising a flow discourager configured to couple to the labyrinth seal component aft end.  
   
   
       12 . The kit of  claim 9 , wherein the forward annular liner and aft liner are configured to form an annular gap therebetween.  
   
   
       13 . The kit of  claim 12 , further comprising a slinger configured to couple to a shaft, the slinger including a plurality of openings formed therein that are configured to communicate with the annular gap.  
   
   
       14 . A method for assembling a combustor assembly, comprising: 
 attaching a first bayonet engagement surface of a first bayonet mount system to a second bayonet engagement surface of the first bayonet mount system, the first bayonet engagement surface formed on an outer annular edge of an aft annular liner, and the second bayonet engagement surface formed on an inner annular edge of a stator forward end; and    engaging a first bayonet engagement surface of a second bayonet mount system with a second bayonet engagement surface of the second bayonet mount system, the first bayonet engagement surface formed on outer annular edge of an forward annular liner, and the second bayonet engagement surface formed on an outer annular edge of the stator forward end.    
   
   
       15 . The method of  claim 14 , further comprising: 
 threading a threaded first end of a labyrinth seal to a threaded inner annular edge of the aft annular liner and axially adjusting the labyrinth seal to mate with at least a portion of a stator aft end, before the step of engaging the first bayonet engagement surface.    
   
   
       16 . The method of  claim 15 , further comprising: 
 coupling a flow discourager to at least a portion of the labyrinth seal, before the step of engaging the first bayonet engagement surface.    
   
   
       17 . The method of  claim 14 , wherein a shaft extends at least partially through the combustor system and the method further comprises the steps of: 
 mounting a slinger to the shaft, the slinger having an annular fuel opening formed therein; and    aligning the slinger fuel opening with an annular gap formed between the forward annular liner and the aft annular liner.    
   
   
       18 . The method of  claim 14 , further comprising: 
 fastening a containment ring to the stator.    
   
   
       19 . The method of  claim 14 , further comprising: 
 coupling the forward annular liner to a compressor section.    
   
   
       20 . The method of  claim 19 , wherein the step of coupling comprises mounting a portion of the forward annular liner inner annular edge to a forward support housing coupled to a compressor housing of the compressor section.