Turbine engine having a combustion section with a fuel nozzle

A turbine engine comprising:

• a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the compressor section defining a compressed air supply having a flow of compressed air, the combustion section comprising:
• a combustion liner and a dome wall collectively forming at least a portion of a combustion chamber, with the dome wall having a fuel nozzle opening;
• and
• a fuel nozzle assembly extending through the fuel nozzle opening, the fuel nozzle assembly comprising:
• a gaseous fuel supply having a flow of gaseous fuel, and a mixer fluidly receiving the flow of gaseous fuel and the flow of compressed air, and outputting a flow of fuel/air mixture;
• a fuel nozzle having a first body defining a centerline axis, the first body defining a first channel fluidly coupled to the mixer to receive the flow of fuel/air mixture, and a second channel fluidly coupled to at least one of the gaseous fuel supply or the compressed air supply, the fuel nozzle including a set of channels fluidly coupling the second channel to the first channel to define the mixer;
• and
• a first swirler provided within the first channel downstream of the mixer;
• wherein the set of channels are axially spaced along the first channel.

A turbine engine comprising:

• a liquid fuel supply having a flow of liquid fuel;
• a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the compressor section defining a compressed air supply having a flow of compressed air, the combustion section comprising:
• a combustion liner and a dome wall collectively forming at least a portion of a combustion chamber, with the dome wall having a fuel nozzle opening;
• and
• a fuel nozzle assembly extending through the fuel nozzle opening, the fuel nozzle assembly comprising:
• a gaseous fuel supply having a flow of gaseous fuel, and a mixer fluidly receiving the flow of gaseous fuel and the flow of compressed air, and outputting a flow of fuel/air mixture;
• a fuel nozzle having a first body defining a centerline axis, the first body defining a first channel fluidly coupled to the mixer to receive the flow of fuel/air mixture, and a second channel fluidly coupled to at least one of the gaseous fuel supply or the compressed air supply;
• a first swirler provided within the first channel downstream of the mixer;
• and
• a heat exchanger fluidly coupled to the compressed air supply and the liquid fuel supply, with a heat transfer between the flow of compressed air and the flow of liquid fuel within the heat exchanger being sufficient to cause a phase change of the flow of liquid fuel to the flow of gaseous fuel,
• wherein the combustion section is configured to operate by:
• supplying the flow of gaseous fuel to the first channel;
• supplying the flow of compressed air to the second channel;
• and
• cooling the flow of gaseous fuel within the first channel through a transfer of heat between the flow of compressed air in the second channel and the flow of gaseous fuel in order to keep the flow of gaseous fuel within the first channel below an auto-ignition temperature of the flow of gaseous fuel.