Patent ID: 9322559
Filing Date: 2016-04-26
CPC Classification: F23D,F23R

Claim Text:
1. A fuel nozzle for a combustor, the fuel nozzle comprising: a nozzle body; an outer sleeve circumferentially surrounding at least a portion of the nozzle body, wherein the outer sleeve and the nozzle body define a premix flow passage therebetween; a first swirler vane circumferentially spaced from a second swirler vane, wherein the first and second swirler vanes extend from the nozzle body to the outer sleeve within the premix flow passage, and a trailing edge of the first and second swirler vanes each form a first angle relative to an axial centerline of the nozzle body; a fuel injection peg having an airfoil shape comprising a leading edge, a trailing edge, a pressure side, and a suction side that extends from the nozzle body to the outer sleeve, wherein the leading edge of the fuel injection peg is positioned downstream from a trailing edge of the first swirler vane and a trialing edge of the second swirler vane within the premix passage, and the trailing edge of each fuel injection peg forming a second angle relative to the axial centerline of the nozzle body that is the same as the first angle; and; a uniform flow region that is formed circumferentially between the first swirler vane and second swirler vane and extends downstream the first and second swirler vanes along a direction of the second angle; wherein the fuel injection peg maintains a radial contour between the nozzle body and outer sleeve that is consistent with a radial contour of the swirler vanes, such that the fuel injection peg is positioned within the uniform flow region, and the leading edge of the fuel injection peg is circumferentially offset from the trailing edge of the first swirler vane and circumferentially offset from the trailing edge of the second swirler vane.