Can-annular gas turbine unit with staged premix-combustion

The invention concerns a gas turbine system, comprising a compressor, at least one combustion chamber (10), and eventually a secondary combustion chamber, for generating working gas. An intermediate turbine may be placed between two combustion chambers. The combustion chamber (15) consists of an individual can-combustor (120) or a number of can-combustors (120) arranged in an annular can-architecture. The can-combustor (120) comprises a number of premixed burners (10) arranged uniformly or divided at least in two groups. One or more groups of the premixed burners (10) may be shifted along the combustor axis with respect to another group, and may also be inclined with respect to the combustor axis. Optional Helmholtz dampers (16) reduce combustion pulsations. Ignition of the mixture starts at the premixed burner outlet. The flame is stabilized in the region of the premixed burner outlet by means of a backflow zone.