Abstract: In a method for operating a gas turbine (GT) with sequential combustion, which has at least one compressor (12, 13), a first combustion chamber (14) with a first turbine (15) which is connected downstream, and a second combustion chamber (16) with a second turbine (17) which is connected downstream, the at least one compressor (12, 13) draws in air and compresses it. The compressed air is fed to the first combustion chamber (14) for combusting a first fuel, and the gas which issues from the first turbine (15) is fed to the second combustion chamber (16) for combusting a second fuel. Increased flexibility and safety in operation is achieved by different fuels being used as first and second fuel.

Abstract: A fuel lance for a gas turbine installation with sequential combustion, in which hot gas is produced in a first combustion chamber and expanded in a subsequent turbine, and then flows through a subsequent second combustion chamber in which the fuel lance for injecting fuel into the hot gas is arranged. The fuel lance has a lance section which extends in the flow direction of the hot gas and includes at least an outer tube which is arranged concentrically to a lance axis, and a center tube which is concentrically arranged in the outer tube and in which the fuel is guided to the lance tip and is injected through first injection openings in the region of the lance tip into the hot gas. The fuel lance is modified for operation with syngas by the first injection openings being arranged directly on the lance tip, and by the first injection openings being oriented so that the fuel jets which emerge from them include an acute angle with the lance axis.