Patent ID: 8365534

Claim:
A combustor for a gas turbine, comprising: an end cover having a nozzle, the nozzle having a front end face and a center axis, the front end face oriented at an inclined end face angle measured with respect to the center axis, the nozzle comprising: a plurality of fuel passages configured for directing fuel in a first direction, wherein the first direction is angled inwardly towards the center axis, fuel exiting the plurality of fuel passages through respective openings located on the front end face; a plurality of oxidizer passages configured for directing oxidizer in a second direction, wherein the second direction is angled outwardly away from the center axis, and wherein the plurality of fuel passages and the oxidizer passages are positioned in relation to one another such that fuel is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor, oxidizer exiting the plurality of oxidizer passages through respective oxidizer opening located on the front end face, a pilot nozzle positioned at the central axis, the pilot nozzle initiating a flame in the burning zone, and wherein the plurality of oxidizer passages are configured to direct oxidizer to create a recirculation zone in the combustor that anchors the burning zone at the front end face of the nozzle, the recirculation zone being downstream of a point of intersection of the fuel and oxidizer from their respective passages.