The invention relates to a tubular combustion chamber system (1) for a gas turbine system (3) with a plurality of annularly arranged transition lines (4) which are designed to be connected with their upstream ends to a burner (10) and through the burner (10) to conduct generated hot gas to a turbine (2), characterized in that the tubular combustion chamber system (1) has a hot gas distributor (5) designed to be connected to the turbine (2) and which defines an annular channel (6) open to the turbine (2), into which the downstream ends of the transition lines (4) open. The invention also relates to a gas turbine system (3) with several burners arranged in a ring, a turbine (2) and a tubular combustion chamber system (1) according to the invention, which connects the burners to the turbine (2).
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