Gas turbine combustor having a fuel nozzle for flame anchoring

A combustor for a gas turbine, the combustor comprising:

• an end cover having at least one nozzle, the nozzle having a front end face and a 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;
• a plurality of cooling flow passages configured for directing working fluid out of one or more of the plurality of cooling flow passage and into the combustor;
• a plurality of oxidizer passages configured for directing oxidizer in a second direction, the second direction being angled outwardly away from the center axis, and wherein the plurality of fuel passages and the plurality of 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, and
• wherein the plurality of oxidizer passages are configured for directing oxidizer to create a recirculation zone that anchors the burning zone at the front end face of the nozzle.

A gas turbine having a combustor, the combustor comprising:

• an end cover having at least one nozzle, the nozzle having a front end face and a center axis, wherein the front end face is oriented at a 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;
• a plurality of cooling flow passages configured for directing working fluid out of the plurality of cooling flow passage and into the combustor;
• 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 oxidizer passages are oriented in an oxidizer angle measured with respect to the front end face of the fuel nozzle, the plurality of fuel passages and the plurality of oxidizer passages being positioned in relation to one another such that fuel supplied to the combustor is in a cross-flow arrangement with oxidizer to create a burning zone in the combustor, and
• wherein the plurality of oxidizer passages are configured for directing oxidizer to create a recirculation zone that anchors the burning zone at the front end face of the nozzle.