Combustor

Abstract

A casing for a combustor of a gas turbine engine has a plurality of apertures, each aperture being reinforced with a band of material dividing the aperture. The casing and reinforcing member are forged simultaneously with the reinforcing member aligned with the direction of maximum stress field.

1 . A combustion casing for use in a gas turbine, the casing having an aperture extending therethrough, wherein the aperture has a reinforcing member extending across and dividing the aperture.  
   
   
       2 . A casing according to  claim 1 , wherein the casing is annular.  
   
   
       3 . A casing according to  claim 1 , wherein the aperture has a rim extending around its periphery.  
   
   
       4 . A casing according to  claim 2 , wherein the rim is raised from a substantially planar area of the casing.  
   
   
       5 . A casing according to  claim 2 , wherein the reinforcing member is integral with the rim.  
   
   
       6 . A casing according to  claim 2 , wherein the rim and the reinforcing member are formed simultaneously by casting, sintering or forging.  
   
   
       7 . A casing according to  claim 2 , wherein the rim is integral with the casing.  
   
   
       8 . A casing according to  claim 2 , wherein the rim and the casing are formed simultaneously by casting, sintering or forging.  
   
   
       9 . A casing according to  claim 2 , wherein the rim is subject to a stress field, the reinforcing member being orientated so as to align with the direction of maximum stress field.  
   
   
       10 . A gas turbine engine incorporating a combustor casing as claimed in  claim 1.