Gas turbine combustion chamber with modified wall thickness

Patent metadata

Field	Value
Publication number	US-2016178198-A1
Application number	US-201514972850-A
Country	US
Kind code	A1
Filing date	Dec 17, 2015
Priority date	Dec 19, 2014
Publication date	Jun 23, 2016
Grant date	—

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.

First claim

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.

Assignees

• Rolls Royce Deutschland

Inventors

• Gerendas Miklos

Classifications

• F23R3/04 Primary

  Air inlet arrangements · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title