Gas turbine combustor having a fuel nozzle for flame anchoring

摘要

A combustor (22) includes an end cover (36) having a nozzle (34). The nozzle (34) has a front end face (60) and a central axis (A-A). The nozzle (34) includes a plurality of fuel passages (62) and a plurality of oxidizer passages (64). The fuel passages (62) are configured for fuel exiting the fuel passage (62). The fuel passages (62) are positioned to direct fuel in a first direction, where the first direction is angled inwardly towards the center axis (A-A). The oxidizer passages (64) are configured for having oxidizer exit the oxidizer passages (64). The oxidizer passages (64) are positioned to direct oxidizer in a second direction, where the second direction is angled outwardly away from the center axis (A-A). The plurality of fuel passages (62) and the plurality of oxidizer passages (64) are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone (110) in the combustor (22).