General Electric Company
Pilot nozzle with inline premixing

Abstract:

A burner for a combustor of a turbomachine includes a pilot nozzle with inline premixing. The pilot nozzle is formed in an aft end of the burner. An air inlet is formed in a forward end of the burner in fluid communication with the pilot nozzle. A mixing channel extends along the axial direction between the air inlet and the pilot nozzle such that the air inlet is in fluid communication with the pilot nozzle via the mixing channel. An annular fuel plenum extends along the circumferential direction. A fuel port is in fluid communication with the annular fuel plenum and the mixing channel, the fuel port includes an outlet configured to inject fuel into the mixing channel such that a shear flow is induced.