Combustion system for gas turbine, has two annular combustion chambers, which are arranged parallel to each other relative to flow direction of combustion gas in coaxial manner

摘要

The combustion system (9) has two annular combustion chambers (10,11), which are arranged parallel to each other relative to the flow direction of a combustion gas in a coaxial manner. The latter annular combustion chamber extends around the former annular combustion chamber. The volume of the latter annular combustion chamber is less than or equal to the volume of the former annular combustion chamber. A gap (12) for cooling air (18) is provided between the two combustion chambers. Independent claims are included for the following: (1) a gas turbine with a turbine inlet; and (2) a method for operating a combustion system.