| 摘要 |
A gas turbine having a burner arrangement (2) with two stages (8, 9) of fuel injectors (3), having a flow direction (S) and having a combustion chamber (5) arranged downstream of the burner arrangement (2), wherein the two stages (8, 9) of fuel injectors (3) are arranged at an angle with respect to the flow direction (S) such that the injected fuel imparts swirl to the flow, wherein one stage (8) has at least one radial (3a) and/or axial (3c) fuel injector and the other stage (9) has at least one tangential (3b) fuel injector, such that the swirl number can be adapted in continuously variable fashion by variation of the pressurization of the two stages (8, 9).
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