Gas turbine engine dual fuel combustor and method of operation

A gas turbine engine for an aircraft, comprising:

• a compressor section;
• a turbine section;
• and
• a combustor that includes:
• an annular combustor shell that includes a front annular liner and a rear annular liner, wherein the front annular liner and the rear annular liner collectively form the combustor shell and define a combustion chamber that includes an inner radial combustion zone and an outer radial combustion zone;
• a plurality of fuel nozzles engaged with the front annular liner and the outer radial combustion zone, wherein the plurality of fuel nozzles are configured to inject a first fuel;
• a rotary fuel slinger engaged with the combustor shell and configured to deliver a second fuel into the inner radial combustion zone;
• wherein the first fuel is a different type of fuel than the second fuel;
• a plurality of first igniters engaged with the outer radial combustion zone and configured to ignite the first fuel;
• and
• a combustor fuel control system that is configured to control delivery of the first fuel to the plurality of fuel nozzles and to control the delivery of the second fuel to the rotary fuel slinger wherein the combustor fuel control system is configured to permit manual switching between a first fuel delivery mode and a second fuel delivery mode.

A method of operating a gas turbine engine for an aircraft, the gas turbine engine including a compressor section, an annular combustor, and a turbine section, wherein the annular combustor includes a combustion chamber having an inner radial combustion zone and an outer radial combustion zone, the method comprising:

• controlling a flow of gaseous zero-carbon fuel to a plurality of fuel nozzles engaged with the outer radial combustion zone of the combustion chamber;
• and
• controlling a flow of liquid aviation fuel to a rotary fuel slinger engaged with the inner radial combustion zone of the combustion chamber;
• wherein the step of controlling the flow of gaseous zero-carbon fuel and the step of controlling the flow of liquid aviation fuel are coordinated so that the flow of gaseous zero-carbon fuel is provided to the plurality of fuel nozzles or the flow of liquid aviation fuel to the rotary fuel slinger based on one or more flight conditions associated with an aircraft powered by the gas turbine engine.