Fuel nozzle for a gas turbine engine

Abstract

A fuel nozzle for a combustor a gas turbine engine includes a flange with a first locator.

What is claimed is: 
     
         1 . A fuel nozzle for a combustor of a gas turbine engine comprising:
 a flange with a first locator.   
     
     
         2 . The fuel nozzle as recited in  claim 1 , wherein said first locator extends from said flange in a Z-direction. 
     
     
         3 . The fuel nozzle as recited in  claim 1 , wherein said first locator is an integral extension. 
     
     
         4 . The fuel nozzle as recited in  claim 1 , wherein said first locator is a pin. 
     
     
         5 . The fuel nozzle as recited in  claim 4 , wherein said pin is fixedly mounted within an aperture in said flange. 
     
     
         6 . The fuel nozzle as recited in  claim 1 , wherein said flange is symmetrical about an X-axis and a Y-axis. 
     
     
         7 . The fuel nozzle as recited in  claim 1 , wherein said first locator is positioned within an extension in said flange. 
     
     
         8 . The fuel nozzle as recited in  claim 1 , wherein said flange include a first and second aperture. 
     
     
         9 . The fuel nozzle as recited in  claim 1 , wherein said flange include a first and second aperture along a common axis. 
     
     
         10 . A combustor section for a gas turbine engine comprising:
 a diffuser case with a fuel injector mount pad having a second locator; and   a fuel injector with a flange having a first locator, said first locator indexed with said second locator.   
     
     
         11 . The combustor section as recited in  claim 10 , wherein said first locator extends from said flange. 
     
     
         12 . The combustor section as recited in  claim 11 , wherein said first locator is a pin. 
     
     
         13 . The combustor section as recited in  claim 10 , wherein said second locator is a slot. 
     
     
         14 . The combustor section as recited in  claim 10 , wherein said first locator is a hole. 
     
     
         15 . The combustor section as recited in  claim 14 , wherein said second locator is a pin. 
     
     
         16 . The combustor section as recited in  claim 10 , wherein said flange includes a first aperture and a second aperture. 
     
     
         17 . A method of mounting a fuel injector into a combustor of a gas turbine engine, comprising:
 bolting a fuel injector flange to a fuel injector pad; and   indexing a first locator that extends from said flange with respect to a second locator defined by said fuel injector pad.   
     
     
         18 . The method as recited in  claim 17 , further comprising: bolting the fuel injector flange to the fuel injector pad with only two (2) bolts.