Patent ID: 6438961
Filing Date: 2002-08-27
Classification: F23C,F23D,F23M

Abstract:
A burner for use in a combustion system of a heavy duty industrial gas turbine, the burner comprising:a fuel/air premixer having an air inlet, a fuel inlet, and an annular mixing passage, the fuel/air premixer mixing fuel and air in the annular mixing passage into a uniform mixture for injection into a combustor reaction zone, wherein the fuel/air premixer comprises a swozzle assembly downstream of the air inlet, the swozzle assembly including a plurality of swozzle assembly turning vanes imparting swirl to the incoming air, and wherein each of the swozzle assembly turning vanes comprises an internal fuel flow passage, the fuel inlet introducing fuel into the internal fuel flow passages; and an inlet flow conditioner disposed at the air inlet of the fuel/air premixer upstream of the fuel inlet, the inlet flow conditioner comprising an inner wall and at least one outer wall defining an annulus therebetween, the at least one outer wall comprising a plurality of perforations, wherein the inlet flow conditioner further comprises at least one annular turning vane, the plurality of perforations and the at least one turning vane controlling a radial and circumferential distribution of incoming air evenly distributing the incoming air about the annulus of the inlet flow conditioner.