Low lump mass combustor wall with quench aperture(s)

Abstract

An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a first layer vertically connected with a second layer. A first portion of the first layer overlaps and is vertically spaced from the second layer by a cavity. A second portion of the first layer is substantially vertically inline with an adjacent portion of the second layer. The second portion of the first layer at least partially forms a quench aperture vertically through the combustor wall.

What is claimed is: 
     
         1 . An assembly for a turbine engine, comprising:
 a combustor wall including a first layer vertically connected with a second layer;   a first portion of the first layer overlapping and vertically offset from a first portion of the second layer; and   a second portion of the first layer at least partially within an aperture in first portion of the second layer, the second portion of the first layer parallel with the first portion of the second layer, and the second portion of the first layer at least partially forming a quench aperture vertically through the combustor wall.   
     
     
         2 . The assembly of  claim 1 , wherein the first layer completely defines the quench aperture vertically through the combustor wall. 
     
     
         3 . The assembly of  claim 1 , wherein the second layer has a uniform thickness. 
     
     
         4 . The assembly of  claim 1 , wherein an annular portion of the first layer extends vertically between the first portion of the first layer and the second portion of the first layer. 
     
     
         5 . The assembly of  claim 4 , wherein the annular portion of the first layer circumscribes the second portion of the first layer. 
     
     
         6 . The assembly of  claim 1 , wherein a vertical thickness of the first portion of the first layer is equal to a vertical thickness of the second portion of the first layer. 
     
     
         7 . The assembly of  claim 1 , wherein the combustor wall extends circumferentially about and axially along a centerline, and the first portion of the first layer is located axially forward of the second portion of the first layer. 
     
     
         8 . The assembly of  claim 1 , wherein the combustor wall extends circumferentially about and axially along a centerline, and the first portion of the first layer is located axially aft of the second portion of the first layer. 
     
     
         9 . The assembly of  claim 1 , wherein a third portion of the first layer overlaps and is vertically spaced from the second layer by the cavity or another cavity, and the second portion of the first layer is between the first portion and the third portion of the first layer. 
     
     
         10 . The assembly of  claim 1 , wherein the second portion of the first layer is partially vertically within the aperture in the second layer. 
     
     
         11 . The assembly of  claim 1 , wherein the second portion of the first layer includes one or more cooling holes. 
     
     
         12 . The assembly of  claim 1 , wherein the second portion of the first layer includes one or more stiffening features. 
     
     
         13 . The assembly of  claim 1 , wherein the second portion of the first layer includes one or more protrusions. 
     
     
         14 . An assembly for a turbine engine, comprising:
 a combustor wall including a first layer vertically connected with a second layer;   a first portion of the first layer overlapping and vertically offset from a first portion of the second layer;   a second portion of the first layer aligned with an aperture extending vertically through the second layer, the second portion of the first layer at least partially forming a quench aperture vertically through the combustor wall; and   an annular portion of the first layer circumscribing the second portion of the first layer, the annular portion of the first layer extending vertically between the first portion of the first layer and the second portion of the first layer.   
     
     
         15 . The assembly of  claim 14 , wherein the second portion of the first layer is parallel with the first portion of the first layer. 
     
     
         16 . The assembly of  claim 14 , wherein the second portion of the first layer is parallel with a portion of the second layer defining the aperture. 
     
     
         17 . The assembly of  claim 14 , wherein a vertical thickness of the first portion of the first layer is equal to a vertical thickness of the second portion of the first layer. 
     
     
         18 . The assembly of  claim 14 , wherein the combustor wall extends circumferentially about and axially along a centerline, and the first portion of the first layer is located axially forward of the second portion of the first layer. 
     
     
         19 . The assembly of  claim 14 , wherein the combustor wall extends circumferentially about and axially along a centerline, and the first portion of the first layer is located axially aft of the second portion of the first layer. 
     
     
         20 . The assembly of  claim 14 , wherein a third portion of the first layer overlaps and is vertically spaced from the second layer by the cavity or another cavity, and the second portion of the first layer is between the first portion of the first layer and the third portion of the first layer.