Gas turbine combustion chamber with modified wall thickness

Abstract

A gas turbine combustion chamber, including at least one combustion chamber wall in which mixed air holes are formed in a predefined area that extends around the combustion chamber in a ring-shaped manner with respect to the central axis of the combustion chamber in a central area of the same, characterized in that the combustion chamber wall has a greater thickness in the ring-shaped area of the mixed air holes than in the areas that are not provided with mixed air holes.

1 . Gas turbine combustion chamber, comprising at least one combustion chamber wall in which mixed air holes are formed in a predefined area that extends around the combustion chamber in a ring-shaped manner with respect to the central axis of the combustion chamber in a central area of the same, wherein the combustion chamber wall has a greater thickness in the ring-shaped area of the mixed air holes than in the areas that are not provided with mixed air holes. 
     
     
         2 . Gas turbine combustion chamber according to  claim 1 , wherein the combustion chamber wall has a substantially constant rigidity in all areas, in particular in the longitudinal direction with respect to the throughflow direction of the combustion chamber. 
     
     
         3 . Gas turbine combustion chamber according to  claim 1 , wherein the greater thickness of the combustion chamber is formed with a wall thickness, wherein the maximal wall thickness is calculated based on the following equation:
     W   max   =C·   √{square root over ((A−Sr)/A)}   ·W   0      W max : maximal wall thickness   W 0 : nominal wall thickness   A: distance between the hole centers of neighboring holes   Sr: sum of the hole radiuses of neighboring holes   C: power factor 0.7 . . . 1.3:   
     
     
         4 . Gas turbine combustion chamber according to  claim 1 , wherein the combustion chamber wall is embodied with a single layer. 
     
     
         5 . Gas turbine combustion chamber according to  claim 1 , wherein the combustion chamber wall is embodied with a double layer, and in that at least one of the combustion chamber walls is provided with a greater wall thickness in the area of the mixed air holes. 
     
     
         6 . Gas turbine combustion chamber according to  claim 1 , wherein the combustion chamber wall is manufactured as a cast part. 
     
     
         7 . Gas turbine combustion chamber according to  claim 1 , wherein the combustion chamber wall is manufactured by means of a generative method. 
     
     
         8 . Gas turbine combustion chamber according to  claim 1 , wherein the combustion chamber wall is manufactured from contoured sheet metal materials. 
     
     
         9 . Gas turbine combustion chamber according to  claim 1 , wherein the combustion chamber wall is manufactured from a fiber-reinforced ceramic material.