annular combustion chamber for a turbomachine

Abstract

An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution an annular flange for fastening to a casing of the turbomachine, the downstream end of the other wall of revolution of the chamber including a bearing mechanism which are spaced apart from another casing of the turbomachine when cold and bear radially on this casing when hot.

1 - 11 . (canceled) 
     
     
         12 . An annular combustion chamber for a turbomachine, the combustion chamber comprising:
 two annular walls forming bodies of revolution, respectively an inner wall and an outer wall, one of the walls including an annular flange for fastening the chamber to a casing of the turbomachine,   wherein the other annular wall include bearing means configured, when cold, to be spaced apart from another casing of the turbomachine, and, when hot, to bear radially against the casing.   
     
     
         13 . An annular combustion chamber according to  claim 12 , wherein the bearing means is connected to the wall of the chamber via at least one elastically-deformable zone. 
     
     
         14 . An annular combustion chamber according to  claim 12 , wherein the bearing means comprises a cylindrical end wall connected to the annular wall of the chamber via a wall that is inclined relative to the axis of the chamber. 
     
     
         15 . An annular combustion chamber according to  claim 14 , wherein the wall inclined relative to the axis of the chamber includes orifices for passing ventilation air. 
     
     
         16 . An annular combustion chamber according to  claim 14 , wherein the wall inclined relative to the axis of the chamber is flexible. 
     
     
         17 . An annular combustion chamber according to  claim 12 , wherein the annular fastener flange carries the outer annular wall, the inner annular wall, and the bearing means via an end wall of the chamber. 
     
     
         18 . An annular combustion chamber according to  claim 12 , wherein the annular fastener flange carries the inner annular wall together with the outer annular wall and the bearing means via a chamber end wall. 
     
     
         19 . A turbomachine, such as an airplane turboprop or turbojet, comprising an annular combustion chamber according to  claim 12 . 
     
     
         20 . A turbomachine according to  claim 19 , further comprising a casing including a cylindrical portion against which the bearing means of the combustion chamber are configured to bear when hot. 
     
     
         21 . A turbomachine according to  claim 19 , wherein, when hot, the bearing means of the combustion chamber makes sliding contact with the cylindrical portion of the casing. 
     
     
         22 . A turbomachine according to  claim 19 , wherein a clearance, when cold, between the bearing means of the combustion chamber and the cylindrical bearing portions of the casing is of an order of one-tenth of a millimeter.