Combustion chamber lining

摘要

A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2 each have a straight hollow tubular profile and are arranged as individual segments At least one hollow metallic body 1 having air-passage holes 5 for the passage of cooling air is provided in each ceramic body 2.