| 摘要 |
The invention relates to a tubular combustion chamber (22) for a gas turbine (1), comprising at least one burner arrangement (11), a housing wall (24) which surrounds the combustion chamber interior and has a flame tube (20) and a transition piece (21) connected to the flame tube on the downstream side. The tubular combustion chamber has high durability and enables low-emission operation of the combustion chamber at particularly low production costs. For this purpose, the housing wall is formed at least in sections as a three-layer composite system (29) with an inner wall layer (31) facing the combustion chamber interior, an intermediate wall layer (32), and an outer wall layer (33) which are connected to one another and comprise cooling channels (30), wherein at least one longitudinal recess (36) is formed in each channel in the intermediate wall layer by means of a laser, which longitudinal recess is fluidically connected to at least one opening (34) in the outer wall layer and to at least one additional opening (35) in a wall layer, wherein, in at least one channel, the longitudinal sides (38) of the recess (36) comprise ribs (42) that are integrally formed with the intermediate wall layer. |
