Methods and apparatus for assembling turbine engines

Abstract

A method for assembling a gas turbine engine includes providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, coupling the turbine nozzle within the gas turbine engine, such that the turbine nozzle is downstream from a combustor, and coupling the turbine nozzle to the combustor using at least a first annular interface seal, wherein the first annular interface seal substantially seals a gap defined between the turbine nozzle and the combustor, and wherein the first annular interface seal includes at least a first ply and a second ply that is coupled to the first ply.

1 . A method for assembling a gas turbine engine, said method comprising: 
 providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands;    coupling the turbine nozzle within the gas turbine engine, such that the turbine nozzle is downstream from a combustor; and    coupling the turbine nozzle to the combustor using at least a first annular interface seal, wherein the first annular interface seal substantially seals a gap defined between the turbine nozzle and the combustor, and wherein the first annular interface seal includes at least a first ply and a second ply that is coupled to the first ply.    
     
     
         2 . A method in accordance with  claim 1  further comprising coupling the turbine nozzle to the combustor using at least a first annular interface seal that includes at least a first metallic ply and a second metallic ply that is coupled to the first metallic ply.  
     
     
         3 . A method in accordance with  claim 1  further comprising coupling the turbine nozzle to the combustor using at least a first annular interface seal that includes at least a first nickel based alloy ply and a second nickel based alloy ply that is coupled to the first nickel based alloy ply.  
     
     
         4 . A method in accordance with  claim 1  further comprising applying a wear coating to at least a portion of the first annular interface seal.  
     
     
         5 . A method in accordance with  claim 1  further comprising applying a wear coating to at least a portion of the turbine nozzle.  
     
     
         6 . A method in accordance with  claim 1  further comprising applying a wear coating to at least a portion of the first annular interface seal and the turbine nozzle.  
     
     
         7 . A turbine engine nozzle assembly for use in a turbine engine including a combustor, said engine nozzle assembly comprising: 
 an outer band comprising a leading edge, a trailing edge, and a body extending therebetween;    an inner band comprising a leading edge, a trailing edge, and a body extending therebetween;    at least one vane extending between said outer and inner bands, said at least one vane comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge, said at least one vane leading edge positioned downstream from said inner and outer band leading edges; and    a system configured to couple said nozzle to the combustor, said system comprising a first annular interface seal coupled between said outer band and the combustor and a second annular interface seal coupled between said inner band and the combustor, said first and second annular interface seals each comprising a first ply and a second ply that is coupled to said first ply.    
     
     
         8 . A turbine engine nozzle assembly in accordance with  claim 7  wherein at least one of said first annular interface seal and said second annular interface seal comprises an L-shaped annular body.  
     
     
         9 . A turbine engine nozzle assembly in accordance with  claim 7  wherein said first and second annular interface seals each comprise a first metallic ply and a second metallic ply that is coupled to said first metallic ply.  
     
     
         10 . A turbine engine nozzle assembly in accordance with  claim 7  wherein said first and second annular interface seals each comprise a first nickel based alloy ply and a second nickel based alloy ply that is coupled to said first nickel based alloy ply.  
     
     
         11 . A turbine engine nozzle assembly in accordance with  claim 7  further comprising a wear coating applied to at least one of said first and second annular interface seals.  
     
     
         12 . A turbine engine nozzle assembly in accordance with  claim 7  further comprising a wear coating applied to at least a portion of said turbine nozzle.  
     
     
         13 . A turbine engine nozzle assembly in accordance with  claim 7  further comprising a wear coating applied to at least one of said first and second annular interface seals and to at least a portion of said turbine nozzle.  
     
     
         14 . A gas turbine engine comprising: 
 a combustor;    a turbine nozzle assembly downstream from and in flow communication with said combustor, said nozzle assembly comprising an outer band, an inner band, at least one vane extending between said outer and inner bands, and a leading edge fillet, said at least one vane comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge; and    a system configured to couple said nozzle to the combustor, said system comprising a first annular interface seal coupled between said outer band and the combustor and a second annular interface seal coupled between said inner band and the combustor, said first and second annular interface seals each comprising a first ply and a second ply that is coupled to said first ply.    
     
     
         15 . A gas turbine engine in accordance with  claim 14  wherein at least one of said first annular interface seal and said second annular interface seal comprises an L-shaped annular body.  
     
     
         16 . A gas turbine engine in accordance with  claim 14  wherein said first and second annular interface seals each comprise a first metallic ply and a second metallic ply that is coupled to said first metallic ply.  
     
     
         17 . A gas turbine engine in accordance with  claim 14  wherein said first and second annular interface seals each comprise a first nickel based alloy ply and a second nickel based alloy ply that is coupled to said first nickel based alloy ply.  
     
     
         18 . A gas turbine engine in accordance with  claim 14  further comprising a wear coating applied to at least one of said first and second annular interface seals.  
     
     
         19 . A gas turbine engine in accordance with  claim 14  further comprising a wear coating applied to at least a portion of said turbine nozzle.  
     
     
         20 . A gas turbine engine in accordance with  claim 14  further comprising a wear coating applied to at least one of said first and second annular interface seals and to at least a portion of said turbine nozzle.