Device in a burner for gas turbines

The present invention relates to a device in a burner gas turbines as appears in the preamble of claim . Device in a burner for gas turbines, comprising a cylindrical housing () and a fuel inlet tube () arranged centrally within said housing, said housing () and fuel inlet tube () mutually defining an annular chamber (). The annular chamber () extending into an extended diameter combustion chamber (), having means () for supplying combustion air to said annular chamber (). Radial flow swirlers () are provided for creating a rotational movement of the combustion air in said annular chamber. The housing () has a downstream restriction () in front of the free end of the centrally located fuel inlet tube (), at the entrance of the combustion chamber (), 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 (). The fuel inlet tube () has a multiple of inlet nozzles () in an array at a distance from the free end of the tube of at least approximately 1,5 times the diameter of the fuel inlet tube. This enable low emissions of NOx and CO over a wide operating range in a low complexity, cost effective configuration.