Patent ID: 6938424
Filing Date: 2005-09-06
Classification: F23M,F23R

Abstract:
1. An annular combustion chamber for a gas turbine extending in the axial direction, comprising: a combustor enclosed by the combustion chamber; a bearing structure arranged on the inside of the combustion chamber and facing the combustor; a lining element having a rear side facing away from the combustor and having two edge areas extending in the axial direction, each said edge area being secured to the bearing structure that lines the annular combustion chamber by and a plurality of interlocking devices separated by a plurality of axial spacing having a width arranged on the lining element such that in order to release the lining element from the bearing structure the lining element is moved by the extent of the width of the interlocking devices in the axial direction, wherein two interlocking devices of the lining element that are immediately adjacent in the axial direction have an axial spacing which is identical to or greater than the width of the interlocking devices.