| 摘要 |
The invention relates to a gas turbine assembly which substantially consists of at least one compressor, at least one first burner (8, 201), at least one second burner (9, 202) that is connected downstream of the first burner, and at least one turbine (5) that is connected downstream of the second burner. At least the first and second burner (8, 9) form a component of a tubular or quasi-tubular combustion chamber element (100, 200, 300) in the flow direction of the combustion path of said burners, said combustion chamber element being closed or quasi-closed and extending between the compressor (2) and the turbine (5). The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring. |
