Methods and apparatus for fabricating gas turbine engine combustors

Abstract

A method facilitates fabricating a gas turbine engine combustor. The method comprises coupling a venturi to a primary swirler, and coupling the venturi to a secondary swirler such that a gap is defined between a portion of the venturi and a portion of one of the primary swirler and the secondary swirler.

1 . A method for fabricating a gas turbine engine combustor, said method comprising: 
 coupling a venturi to a primary swirler; and    coupling the venturi to a secondary swirler such that a gap is defined between a portion of the venturi and a portion of one of the primary swirler and the secondary swirler.    
   
   
       2 . A method in accordance with  claim 1  wherein coupling the venturi to a secondary swirler comprises coupling the venturi to the secondary swirler such the venturi is coupled between the primary and secondary swirlers and such that a slide fit is defined between at least a portion of the venturi and a portion of one of the primary and secondary swirlers.  
   
   
       3 . A method in accordance with  claim 1  wherein coupling the venturi to a secondary swirler comprises coupling the venturi to one of the primary swirler and the secondary swirler using at least one of a brazing operation and a welding operation.  
   
   
       4 . A method in accordance with  claim 1  wherein one of the primary swirler and the secondary swirler defines a flow passage extending therethrough, said method further comprises forming a plurality of openings extending in flow communication between the flow passage and the gap.  
   
   
       5 . A method in accordance with  claim 1  further comprising coating the portion of the venturi defining the gap with a thermal barrier coating.  
   
   
       6 . A method in accordance with  claim 1  wherein coupling the venturi to a secondary swirler further comprises coupling the venturi to the secondary swirler such that the venturi extends between the primary and secondary swirlers.  
   
   
       7 . A combustor for a gas turbine engine, said combustor comprising: 
 a venturi; and    a secondary swirler extending circumferentially around said venturi, said secondary swirler coupled to said venturi such that a gap is defined between a portion of said secondary swirler and said venturi.    
   
   
       8 . A combustor in accordance with  claim 7  further comprising a primary swirler coupled to said venturi such that said venturi is between said primary and secondary swirlers.  
   
   
       9 . A combustor in accordance with  claim 8  wherein at least a portion of said venturi is slidably coupled to a portion of one of said primary and said secondary swirlers.  
   
   
       10 . A combustor in accordance with  claim 8  wherein at least a portion of said venturi is coupled to a portion of one of said primary and said secondary swirlers in a slide fit, said slide fit facilitates accommodating thermal growth of at least one of said primary and said secondary swirler with respect to said venturi.  
   
   
       11 . A combustor in accordance with  claim 7  wherein said secondary swirler comprises a secondary air passage extending therethrough and a plurality of openings, said openings couple said secondary air passage and said gap in flow communication.  
   
   
       12 . A combustor in accordance with  claim 7  wherein said gap is defined between a radially outer surface of said venturi and a radially inner surface of said secondary swirler, said venturi radially outer surface comprises a layer of thermal barrier coating.  
   
   
       13 . A combustor in accordance with  claim 7  wherein said gap facilitates reducing an operating temperature of said venturi.  
   
   
       14 . A gas turbine engine comprising a combustor comprising at least one annular air swirler and an annular venturi, said annular air swirler coupled to said venturi such that a gap is defined between a portion of said air swirler and said venturi.  
   
   
       15 . A gas turbine engine in accordance with  claim 14  wherein said gap facilitates reducing an operating temperature of said venturi.  
   
   
       16 . A gas turbine engine in accordance with  claim 14  wherein at least a portion of said at least one annular air swirler is coupled in a slide fit against said venturi.  
   
   
       17 . A gas turbine engine in accordance with  claim 14  wherein said air swirler defines a flow passageway extending therethrough, said at least one air swirler comprises a plurality of openings extending in flow communication between said flow passageway and said gap.  
   
   
       18 . A gas turbine engine in accordance with  claim 14  wherein said gap facilitates maintaining an operating temperature of said venturi below a predetermined temperature.  
   
   
       19 . A gas turbine engine in accordance with  claim 14  wherein said gap facilitates reducing coking of said venturi.  
   
   
       20 . A gas turbine engine in accordance with  claim 14  wherein said at least one air swirler comprises a primary swirler and a secondary swirler, said venturi coupled between said primary and secondary swirlers.