Axial swirler for a gas turbine burner

A method of using an axial swirler for a gas turbine burner, the axial swirler comprising a vane ring with a plurality of swirler vanes circumferentially distributed around a swirler axis and extending in a radial direction between an inner radius and an outer radius, each of said swirler vanes comprising a trailing edge configured to define a controlled distribution of an exit flow velocity profile and/or a fuel equivalence ratio in the radial direction, the trailing edge extending between the inner radius and the outer radius of the swirler vane opposite a leading edge of the swirler vane, wherein said trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius to define an apex along the trailing edge, a first segment of the trailing edge extending from the inner radius to the apex and a second segment of the trailing edge extending from the apex to the outer radius, the method comprising:

• passing fluid along each of the swirler vanes such that at the inner radius of the trailing edge of the swirler vane an exit flow angle of the fluid passing along the swirler vane between a tangent to the camber line of the swirler vane and the swirler axis is between 0° and 30°, the exit flow angle is linearly increasing to a value of between 30° and 60° from the inner radius to the predetermined radius of the trailing edge, and the exit flow angle is linearly decreasing to a value of between 10° and 40° from the predetermined radius to an outer radius of the trailing edge of the swirler vane.