Methods and apparatus for assembling turbine engines

Abstract

A method facilitates the assembly of a gas turbine engine. The method of assembly comprises 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 ring, wherein the first annular ring substantially seals a gap defined between the turbine nozzle and the combustor.

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 ring, wherein the first annular ring substantially seals a gap defined between the turbine nozzle and the combustor.    
     
     
         2 . A method in accordance with  claim 1  wherein providing a turbine nozzle further comprises biasing the first annular ring to maintain sealing contact with the turbine nozzle.  
     
     
         3 . A method in accordance with  claim 2  wherein the outer band includes a forward flange that extends substantially perpendicularly from an outer surface of the nozzle assembly, biasing the first annular ring further comprises biasing the first annular ring in sealing contact against the forward flange.  
     
     
         4 . A method in accordance with  claim 2  wherein biasing the first annular ring to maintain sealing contact further comprises biasing the second annular ring against a forward flange extending from the inner band.  
     
     
         5 . A method in accordance with  claim 2  wherein biasing the first annular ring to maintain sealing contact further positioning a biasing mechanism to bias the first annular ring in sealing contact against a flange extending radially outward from one of the outer band and the inner band.  
     
     
         6 . 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 retention system configured to couple said nozzle to the combustor, said retention system comprising a first annular ring coupled between said outer band and the combustor, and a second annular ring coupled between said inner band and the combustor.    
     
     
         7 . A turbine engine nozzle assembly in accordance with  claim 6  wherein at least one of said first annular ring and said second annular ring comprises an L-shaped annular body.  
     
     
         8 . A turbine engine nozzle assembly in accordance with  claim 6  wherein at least one of said outer band and said inner band further comprises an arcuate forward flange extending substantially radially outward from an outer surface of said band.  
     
     
         9 . A turbine engine nozzle assembly in accordance with  claim 8  wherein at least one of said first annular ring and said second annular ring is coupled in sealing contact against a downstream surface of said band forward flange.  
     
     
         10 . A turbine engine nozzle assembly in accordance with  claim 6  wherein at least one of said inner band and said outer band further comprises a forward flange extending substantially radially outward from an outer surface of said band and a retention tab extending substantially radially outward from said outer surface of said outer band, said tab spaced a distance downstream from said forward flange such that a retention slot is defined therebetween.  
     
     
         11 . A turbine engine nozzle assembly in accordance with  claim 10  wherein at least one of said first annular ring and said second annular ring is securely coupled within said retention slot in sealing contact against a downstream surface of said forward flange.  
     
     
         12 . A turbine engine nozzle assembly in accordance with  claim 10  wherein said retention system further comprises a biasing mechanism configured to bias at least one of said first annular ring and said second annular ring in sealing contact with said forward flange.  
     
     
         13 . A turbine engine nozzle assembly in accordance with  claim 6  wherein said retention system further comprises a biasing mechanism configured to bias at least one of said first annular ring and said second annular ring into contact with at least one of said inner band and said outer band.  
     
     
         14 . A gas turbine engine comprising: 
 a combustor; and    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 retention system configured to couple said nozzle assembly to said combustor, said retention system comprising a first annular ring coupled between said outer band and said combustor, and a second annular ring coupled between said inner band and said combustor.    
     
     
         15 . A gas turbine engine in accordance with  claim 14  wherein at least one of said turbine nozzle assembly inner band and said outer band comprises a forward flange extending substantially radially outward from an outer surface of said band, at least one of said first annular ring and said second annular ring is coupled against said forward flange.  
     
     
         16 . A gas turbine engine in accordance with  claim 14  wherein said first annular band and said second annular band substantially seal a gap between said turbine nozzle assembly and said combustor.  
     
     
         17 . A gas turbine engine in accordance with  claim 14  wherein at least one of said first annular ring and said second annular ring comprise an L-shaped cross sectional profile.  
     
     
         18 . A gas turbine engine in accordance with  claim 14  wherein at least one of said inner band and said outer band comprises a forward flange extending substantially radially outward from an outer surface of said band, and a retention tab extending substantially radially outward from said outer surface, said retention tab between said forward flange and said trailing.  
     
     
         19 . A gas turbine engine in accordance with  claim 18  wherein said retention system further comprises a biasing mechanism configured to bias at least one of said first annular ring and said second annular ring in against said forward flange.  
     
     
         20 . A gas turbine engine in accordance with  claim 14  wherein said first annular ring is coupled in sealing contact to said outer band, said second annular ring is coupled in sealing contact with said inner band.