| 摘要 |
PROBLEM TO BE SOLVED: To provide an axial swirler for a gas turbine burner, which allows creation of an optimal exit flow velocity profile for increased combustion stability.SOLUTION: In order to achieve a controlled distribution of an exit flow velocity profile and/or a fuel equivalence ratio in the radial direction, a trailing edge 22, 35 is discontinuous with the trailing edge 22, 35 having a discontinuity 27 at a predetermined radius (R); at an inner radius (R), an exit flow angle (α), i.e. the angle between the tangent to the camber line of a vane 19, 19b, 33a, 33b and a swirler axis, is between 0° and 30°; and the exit flow angle (α) from the inner radius (R) is increasing to a value of between 30° and 60° at the predetermined radius (R), and the angle (α) from this predetermined radius (R) is decreasing to a value of between 10° and 40° at an outer radius (R). |
