Abstract: Device in a burner for gas turbines, comprising a cylindrical housing (10) and a fuel inlet tube (16) arranged centrally within said housing, said housing (10) and fuel inlet tube (16) mutually defining an annular chamber (28). The annular chamber (28) extending into an extended diameter combustion chamber (18), having means (25) for supplying combustion air to said annular chamber (28). Radial flow swirlers (14) are provided for creating a rotational movement of the combustion air in said annular chamber. The housing (10) has a downstream restriction (20) in front of the free end of the centrally located fuel inlet tube (16), at the entrance of the combustion chamber (18), for creating a rich combustion spinning tubular swirl dominated flow of a mixture of air and fuel, with a recirculation central core, said tubular spinning flow extending into the combustion chamber (18).

Abstract: A fuel/air mixing device for two-stage, lean-flow, pre-mix combustion chambers in gas turbines. The primary and secondary combustors are formed as venturi nozzles with the primary venturi mounted tangentially to a flametube which surrounds the secondary venturi. A perforated cone is provided at the free end of the secondary venturi for the penetration of the fuel-air mixture into the primary flame.