HYBRID COMBUSTOR WITH STAGED INJECTION OF PRE-MIXED FUEL

摘要

HYBRID COMBUSTOR WITH STAGEDINJECTION OF PRE-MIXED FUELABSTRACT OF THE DISCLOSUREA combustor for a gas turbine engine which includesa fuel nozzle at the head end of the combustor, to provide adiffusion flame, and downstream inlet means at a pluralityof axial dimensions of the combustor to inject pre-mixedlean fuel/air into the combustor for admission downstreamfrom the diffusion flame resulting in a series of low temper-ature premixed flames to provide relatively high turbineinlet temperature from the combustor with a minimum ofthermally formed NOx compounds.