Burner for gas turbine engines with axially adjustable swirler

A burner having a fuel nozzle for gas turbine engines, comprising:

• a ring-shaped swirling device coaxially arranged radially outward from a longitudinal axis through said fuel nozzle, said swirling device having an outer and an inner annular surface;
• flow ducts equidistantly spaced along a circumference of said ring-shaped swirling device for an adjustable feeding of combustion air, said flow ducts extending through said swirling device from the outer to the inner annular surface thereof in a skewed direction with respect to a radial from said longitudinal axis;
• said ring shaped swirling device including two ring members, each having profiled sections formed by profiled surfaces extending in an axial direction of said burner, said flow ducts being formed between opposingly facing radially extending ones of said profiled surfaces;
• wherein corresponding profiled sections formed by said profiled surfaces are arranged to be axially movable relative to one another by said two ring members;
• wherein one of said corresponding profiled sections is a hollow body into which the other said corresponding profiled section engages in a movable manner such that said flow ducts maintain a constant cross-section over their entire axial length for adjustment between minimal and maximal flow rates of said combustion air.