Patent ID: 8240150

Claim:
A nozzle for a gas turbine combustor comprising: a first radially outer tube defining a first passage having an inlet and an outlet, said inlet adapted to supply premix air to a reaction zone of the combustor; a center body within said first radially outer tube, said center body comprised of a second radially intermediate tube within said first radially outer tube for supplying fuel to the reaction zone and a third radially inner tube for supplying additional air to the reaction zone; wherein said second intermediate tube has a first outlet end closed by a first end wall that is formed with a plurality of substantially parallel, axially-oriented air outlet passages for the additional air in the third radially inner tube, each air outlet passage having a respective plurality of associated fuel outlet passages in said first end wall for the fuel in the second radially intermediate tube, and further wherein said respective plurality of associated fuel outlet passages have non-parallel center axes that intersect a center axis of the respective air outlet passage adapted to locally mix fuel and air exiting said center body.