Combustion chamber cooling

Abstract

A gas turbine combustion chamber ( 8 ) surrounded by an inner wall ( 2 ) having cooling air bores ( 17 ) and an outer wall ( 9 ) that is spaced from the inner wall ( 2 ). The outer wall ( 9 ) likewise has cooling air bores ( 16 ) and is formed of a plurality of wall elements ( 11 ) that are arranged in the circumferential direction of the gas turbine combustion chamber ( 8 ) essentially next to each other. The outer wall elements are arranged on the inner wall ( 2 ) by means of a fixed bearing ( 24 ) on one narrow side ( 21 ) of a wall element and by means of a floating bearing ( 25 ) on an opposite narrow side ( 21 ) of the element, configured to define a hollow space ( 10 ) is formed between the two walls ( 2, 9 ).

1 . A gas turbine combustion chamber comprising:
 an inner wall around the chamber, first cooling air bores through the inner wall;   an outer wall around and spaced above the inner wall, second cooling air bores through the outer wall;   the outer wall is formed from multiple separate wall elements which are arranged substantially next to one another in the circumferential direction of the gas turbine combustion chamber, the wall elements having opposite, axially extending, narrow sides and are spaced above the inner wall;   a respective fixed bearing located on one of the narrow sides of each wall element and supporting the respective narrow side of the wall element on and spaced above the inner wall and the fixed bearing being configured to hold the wall element against shifting circumferentially; and   a floating bearing on the opposite narrow side of each of the wall elements, the fixed and floating bearings being configured to support the neighboring wall elements with respect to the inner wall such that a cavity is formed between the inner and outer walls; and   adjacent wall elements are arranged such that they overlap in the circumferential direction.   
     
     
         2 . The gas turbine combustion chamber as claimed in  claim 1 , wherein the outer wall elements are supported on and located above the inner wall by the fixed bearing toward a burner side of the wall elements and by the floating bearing on the turbine side of the wall elements. 
     
     
         3 . The gas turbine combustion chamber as claimed in  claim 1 , wherein the inner wall is in the form of a hollow frustum and the wall elements are in the form of hollow frustum segments. 
     
     
         4 . The gas turbine combustion chamber as claimed in  claim 1 , wherein the floating bearing is comprised of ring segments which each have a groove located and configured for receiving one narrow side of adjacent ones of the wall elements and the groove is configured to allow the respective narrow sides received in the respective groove to move in the groove due to temperature variation. 
     
     
         5 . The gas turbine combustion chamber as claimed in  claim 1 , wherein the fixed bearing is comprised of ring segments around the inner wall. 
     
     
         6 . The gas turbine combustion chamber as claimed in  claim 2 , wherein at least one of the bearings has cooling air bores. 
     
     
         7 . The gas turbine combustion chamber as claimed in  claim 1 , further comprising retainers located in the region where each two adjacent wall elements overlap and configured to prevent the two adjacent wall elements from separating. 
     
     
         8 . The gas turbine combustion chamber as claimed in  claim 7 , wherein the retainers are attached to the inner wall. 
     
     
         9 . The gas turbine combustion chamber as claimed in  claim 8 , further comprising the wall elements have openings for the retainers to extend through the openings, and diameters of the retainer openings in each two adjacent wall elements are larger than the diameters of the retainers for their adjacent wall elements. 
     
     
         10 . The gas turbine combustion chamber as claimed in  claim 1 , further comprising spacers between the inner wall and the outer wall located to prevent contact between the inner and outer walls. 
     
     
         11 . The gas turbine combustion chamber as claimed in  claim 10 , wherein the spacers are arranged on the inner wall and located opposite a central region of the respective wall element. 
     
     
         12 . The gas turbine combustion chamber as claimed in of  claim 1 , wherein a cavity is formed between the inner wall and the outer wall and is embodied as an acoustic damper. 
     
     
         13 . The gas turbine combustion chamber as claimed in  claim 2 , wherein the floating bearing receives the narrow axial sides of each two neighboring outer wall elements to overlap in the floating bearing. 
     
     
         14 . The gas turbine combustion chamber as claimed in  claim 3 , wherein the floating bearing of each outer wall element is toward a wider end of the frustum and the fixed bearing of each outer wall element is toward a narrow end of the frustum. 
     
     
         15 . The gas turbine combustion chamber as claimed in  claim 2 , wherein the fixed bearing is welded to the inner wall.