Gas turbine engine and fuel nozzle assembly therefor
A gas turbine engine, comprising a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising: a combustor liner that at least partially defines a combustion chamber; and a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber and comprising: a rich fuel supply configured to provide a rich mixture of gaseous fuel and air; a lean fuel supply configured to provide a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture; a rich fluid passage fluidly coupled to the rich fuel supply to emit the rich mixture into the combustion chamber; and a lean fluid passage fluidly coupled to the lean fuel supply to emit the lean mixture into the combustion chamber.
1 . A gas turbine engine, comprising:
a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising:
a combustor liner that at least partially defines a combustion chamber, the combustion chamber defining a centerline; and
a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber and comprising:
a rich fuel supply including a rich mixture of gaseous fuel and air;
a lean fuel supply including a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture;
a rich fluid passage fluidly coupled to the rich fuel supply and emitting the rich mixture in a direction towards the centerline of the combustion chamber into the combustion chamber; and
a lean fluid passage fluidly coupled to the lean fuel supply and emitting the lean mixture in a direction away from the centerline of the combustion chamber into the combustion chamber;
wherein the combustion section includes a wall coupled to the combustor liner;
wherein the gaseous fuel nozzle assembly includes at least a portion of the wall; and
wherein the combustor liner includes a height at the wall;
wherein a ratio of a lean fluid passage diameter of the lean fluid passage to the height of the combustor liner is at least 0.3 and less than or equal to 0.8;
wherein a ratio of a rich fluid passage diameter of the rich fluid passage to the height of the combustor liner is at least 0.1 and less than or equal to 0.6.
2 . The gas turbine engine of claim 1 , wherein the rich mixture of gaseous fuel and air has a first equivalence ratio greater than 4 and less than or equal to 10.
3 . The gas turbine engine of claim 2 , wherein the lean mixture of gaseous fuel and air has a second equivalence ratio of greater than 0 and less than or equal to 0.4.
4 . The gas turbine engine of claim 3 , wherein the gaseous fuel is hydrogen gas.
5 . The gas turbine engine of claim 1 , wherein the rich fluid passage and the lean fluid passage are annular and concentric.
6 . The gas turbine engine of claim 5 , wherein a rich fluid passage output of the rich fluid passage is disposed radially inward of a lean fluid passage output of the lean fluid passage.
7 . The gas turbine engine of claim 1 , wherein the lean fluid passage and the rich fluid passage are configured to provide an amount of air to the combustion chamber; and
wherein the rich fluid passage provides at least 5% and less than or equal to 25% of the amount of air to the combustion chamber.
8 . The gas turbine engine of claim 1 , wherein the rich fluid passage is configured to generate an inside-out recirculation of the rich mixture in the combustion chamber;
wherein the lean fluid passage to configured to generate an outside-in recirculation of the lean mixture in the combustion chamber; and
wherein the gaseous fuel nozzle assembly and the combustor liner are configured such that the outside-in recirculation overlaps with the inside-out recirculation.
9 . The gas turbine engine of claim 1 , further comprising a second gaseous fuel nozzle assembly disposed adjacent the gaseous fuel nozzle assembly.