Apparatus for fabricating gas turbine engine combustors

Abstract

A method facilitates manufacturing a combustor for a gas turbine engine. The combustor includes an inner and an outer liner, a dome, and flanges. The method comprises assembling the inner and outer liner such that each includes a series of liner panels, positioning a spatter shield against a downstream side of the inner and outer liners, wherein the spatter shield comprises molybdenum, positioning a mounting flange against the downstream side of the inner and outer liners, such that the spatter shield is positioned at least partially between the mounting flange and the inner and outer liners, and coupling the mounting flange to the inner and outer liners.

What is claimed is:  
     
         1 . A method for manufacturing a combustor for a gas turbine engine, the combustor including an inner and an outer liner, said method comprising: 
 assembling the inner and outer liner such that each includes a series of liner panels;    positioning a spatter shield against a downstream side of the inner and outer liners, wherein the spatter shield comprises molybdenum;    positioning a mounting flange against the downstream side of the inner and outer liners, such that the spatter shield is positioned at least partially between the mounting flange and the inner and outer liners; and    coupling the mounting flange to the inner and outer liners.    
     
     
         2 . A method in accordance with  claim 1  wherein coupling the mounting flange to the inner and outer liners comprises coupling the mounting flange to the inner and outer liners using electron beam welding.  
     
     
         3 . A method in accordance with  claim 2  wherein positioning a spatter shield against a downstream side of the inner and outer liners comprises positioning a spatter shield aft of a weld joint to be formed.  
     
     
         4 . A method in accordance with  claim 2  wherein positioning a spatter shield against a downstream side of the inner and outer liners comprises positioning the spatter shield to facilitate preventing the electron beam from melting the inner and outer liner panels.  
     
     
         5 . A method in accordance with  claim 1  wherein positioning a mounting flange against the downstream side of the inner and outer liners comprises removably coupling the spatter shield to the mounting flange with at least one fastener.  
     
     
         6 . A method in accordance with  claim 1  wherein positioning a spatter shield against a downstream side of the inner and outer liners comprises positioning the spatter shield to facilitate shielding at least a portion of the combustor liner panels while the mounting flange is coupled to the outer and inner liners.  
     
     
         7 . A method in accordance with  claim 1  wherein positioning a spatter shield against a downstream side of the inner and outer liners comprises positioning the spatter shield to facilitate preventing weld heat affected zone (HAZ) cracking during welding of the mounting flange to the combustor outer and inner liners.  
     
     
         8 . A spatter shield for use in manufacturing a gas turbine engine combustor, said spatter shield comprising molybdenum.  
     
     
         9 . A spatter shield in accordance with  claim 6  wherein said spatter shield is formed from a plurality of arcuate pieces.  
     
     
         10 . A spatter shield in accordance with  claim 6  wherein the gas turbine engine combustor is welded, said molybdenum for preventing secondary welding between said shield and the gas turbine engine combustor components being welded.  
     
     
         11 . A spatter shield in accordance with  claim 6  wherein the gas turbine engine combustor includes at least one combustor panel, said spatter shield configured to shield at least one combustor panel during welding.  
     
     
         12 . A spatter shield in accordance with  claim 6  wherein said spatter shield configured to facilitate preventing weld cracking during electron beam welding.  
     
     
         13 . A spatter shield in accordance with  claim 6  wherein said spatter shield configured to facilitate preventing weld heat affected zone (HAZ) cracking during welding.  
     
     
         14 . A spatter shield in accordance with  claim 6  wherein the gas turbine engine includes at least one combustor liner panel, said shield removably coupled by a fastener to the liner panel and configured to shield at least a portion of the liner panel before a flange is welded to the at least one panel.  
     
     
         15 . Apparatus for shielding a portion of a gas turbine engine combustor during assembly, said apparatus comprising a body comprising molybdenum.  
     
     
         16 . Apparatus in accordance with  claim 15  wherein said body comprising a plurality of arcuate members coupled together.  
     
     
         17 . Apparatus in accordance with  claim 15  wherein said apparatus removably coupled to the combustor by at least one fastener for preventing secondary welding between said apparatus and the gas turbine engine combustor components being welded.  
     
     
         18 . Apparatus in accordance with  claim 15  wherein said apparatus further configured to facilitate preventing weld cracking during electron beam welding.  
     
     
         19 . Apparatus in accordance with  claim 15  wherein said apparatus further configured to facilitate preventing weld heat affected zone (HAZ) cracking during welding.