Disclosed is an axial swirler (14b) for a gas turbine burner, which comprises a vane ring which has multiple swirler vanes (19b) distributed in the direction of the circumference around a swirler axis (11). Each of the swirler vanes (19b) comprises a rear edge (22). To achieve a discharge flow speed profile and/or a controlled distribution of a fuel equivalence ratio in a radial direction, the rear edge (22) is discontinuous, and, the rear edge (22) has a discontinuity in a certain radius.;COPYRIGHT KIPO 2016
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