General Electric Company
Premixed fuel nozzle

Abstract:

A fuel injector assembly for a gas turbine engine includes a centerbody extended along a lengthwise direction, the centerbody defining a first fuel nozzle, and an annular shroud defining a second fuel nozzle directly surrounding the centerbody and extended along the lengthwise direction. A passage is defined through the annular shroud and extended generally along the lengthwise direction. The passage defines an exit opening disposed at a downstream end adjacent to the combustion chamber and in fluid communication therewith. The annular shroud defines a fuel inlet opening disposed at an upstream end of the passage. The annular shroud defines an air inlet opening in fluid communication with the passage. The air inlet opening is disposed between the fuel inlet opening and the exit opening.