Gas turbine and method for injecting fuel

摘要

The turbine (1) has a burner arrangement (2) comprising a fuel injector (3), and a combustion chamber (5) arranged downstream of the burner arrangement. The fuel injector is arranged at an angle to a flow direction (S) such that the injected fuel impresses twist on the fuel flow. The burner arrangement is arranged concentrically to a rotational axis or a symmetrical axis (R). Air inlets (6) are arranged in an area of the burner arrangement such that fuel-air-mixture is formed in a premixing path (4), where the fuel injector is arranged in an area of an end of a pipe. An independent claim is also included for a method for injecting fuel into a gas turbine.