Patent ID: 9518740
Filing Date: 2016-12-13
CPC Classification: F23C,F23R

Claim Text:
1. 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 that extends between the inner radius and the outer radius of the swirler vane, the trailing edge configured to define a controlled distribution of an exit flow velocity profile and/or a fuel equivalence ratio in the radial direction, wherein said trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius to define an apex of 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, wherein the trailing edge is configured so that at the inner radius an exit flow angle of fluid passing along the swirler vane between a tangent to a camber line of the swirler vane and a 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, and the exit flow angle is linearly decreasing to a value of between 10° and 40° from the predetermined radius to the outer radius.