Patent ID: 6725666
Filing Date: 2004-04-27
Classification: F23R

Abstract:
A combustion chamber arrangement for gas turbines, comprisingan annular combustion chamber wall having a double-shell construction, with an inner shell and an outer shell, with a gap space being defined by the inner shell and outer shell through which a cooling medium can flow there between, at least one burner connected to one end of the annular combustion chamber leading into a turbine space, and wherein the inner shell being composed of lining elements having longitudinal sides and being releasably arranged on the outer shell, wherein the lining elements are of trapezoidal design and are connected to a supporting structure of the outer shell by pushing a fastening structure into a mating structure in a direction along the longitudinal sides and wherein the lining elements having wide end faces and narrower ends faces wherein the lining elements are all arranged so as to be oriented with the wider end faces in the direction of the burner and the narrower end faces in the direction of the turbine space and wherein a longitudinal groove is arranged on the wider end face of the lining elements as further fastening structure.