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The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel injection system positioned within the head end plenum and upstream of the premi

The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel injection system positioned within the head end plenum and upstream of the premixer. The injection system may be configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel. The injection system also may be configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. The present application and the resultant patent also provide a related method of operating a dual fuel combustor.

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1. A dual fuel combustor for a gas turbine engine, the combustor comprising: a primary premixer positioned within a head end plenum of the combustor; anda dual fuel injection system positioned within the head end plenum and upstream of the premixer and comprising at least one toroidal injection mani

1. A dual fuel combustor for a gas turbine engine, the combustor comprising: a primary premixer positioned within a head end plenum of the combustor; anda dual fuel injection system positioned within the head end plenum and upstream of the premixer and comprising at least one toroidal injection manifold extending about a circumference of the premixer, the toroidal injection manifold comprising: an external sleeve having a toroidal shape and an internal space defined between an inner wall and an outer wall of the external sleeve; andan internal sleeve having a toroidal shape and positioned within the internal space of the external sleeve;wherein the injection system is configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel; andwherein the injection system is configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. 2. The dual fuel combustor of claim 1, wherein the premixer comprises a micro-mixer comprising a plurality of micro-mixer tubes positioned about at least one fuel tube. 3. The dual fuel combustor of claim 1, wherein the toroidal injection manifold further comprises at least one fuel injector extending through the external sleeve and into the internal sleeve. 4. The dual fuel combustor of claim 1, wherein the internal sleeve is configured to receive a flow of the liquid fuel therein, and wherein the external sleeve is configured to direct a flow of air against the internal sleeve such that the liquid fuel vaporizes within the internal sleeve. 5. The dual fuel combustor of claim 4, wherein the external sleeve comprises a plurality of holes extending therethrough and configured to direct the flow of air against the internal sleeve. 6. The dual fuel combustor of claim 1, wherein the external sleeve supports the toroidal injection manifold within the head end plenum. 7. The dual fuel combustor of claim 1, wherein the internal sleeve comprises an inlet extending along a circumference of the internal sleeve, an outlet extending along an opposite circumference of the internal sleeve, and a circumferential shield extending between the inlet and the outlet. 8. The dual fuel combustor of claim 1, wherein the at least one toroidal injection manifold comprises an outer toroidal injection manifold extending about an outer circumference of the premixer and configured to inject the gas fuel or the liquid fuel radially inward about the inlet end of the premixer. 9. The dual fuel combustor of claim 1, wherein the at least one toroidal injection manifold comprises an inner toroidal injection manifold extending about an inner circumference of the premixer and configured to inject the gas fuel or the liquid fuel radially outward about the inlet end of the premixer. 10. The dual fuel combustor of claim 1, wherein the at least one toroidal injection manifold comprises an inner toroidal injection manifold and an outer toroidal injection manifold, and wherein a fuel split ratio between the inner toroidal injection manifold and the outer toroidal injection manifold is 4 to 1. 11. A method of operating a dual fuel combustor, the method comprising: directing a flow of air into a dual fuel injection system positioned within a head end plenum of the combustor, the injection system comprising at least one toroidal injection manifold comprising: an external sleeve having a toroidal shape and an internal space defined between an inner wall and an outer wall of the external sleeve; andan internal sleeve having a toroidal shape and positioned within the internal space of the external sleeve;directing a flow of liquid fuel into the injection system;vaporizing the flow of liquid fuel within the injection system;injecting the flow of vaporized fuel about an inlet end of a primary premixer. 12. A gas turbine engine system, comprising: a compressor;a dual fuel combustor in communication with the compressor; anda turbine in communication with the combustor;wherein the combustor comprises: a primary premixer positioned within a head end plenum of the combustor; anda dual fuel injection system positioned within the head end plenum and upstream of the premixer and comprising at least one toroidal injection manifold extending about a circumference of the premixer, the toroidal injection manifold comprising:an external sleeve having a toroidal shape and an internal space defined between an inner wall and an outer wall of the external sleeve; andan internal sleeve having a toroidal shape and positioned within the internal space of the external sleeve;wherein the injection system is configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel; andwherein the injection system is configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. 13. The system of claim 12, wherein the premixer comprises a micro-mixer comprising a plurality of micro-mixer tubes positioned about at least one fuel tube. 14. The system of claim 12, wherein the toroidal injection manifold further comprises at least one fuel injector extending through the external sleeve and into the internal sleeve. 15. The system of claim 12, wherein the internal sleeve is configured to receive a flow of the liquid fuel therein, and wherein the external sleeve is configured to direct a flow of air against the internal sleeve such that the liquid fuel vaporizes within the internal sleeve. 16. The system of claim 15, wherein the external sleeve comprises a plurality of holes extending therethrough and configured to direct the flow of air against the internal sleeve. 17. The system of claim 12, wherein the internal sleeve comprises an inlet extending along a circumference of the internal sleeve, an outlet extending along an opposite circumference of the internal sleeve, and a circumferential shield extending between the inlet and the outlet. 18. The system of claim 12, wherein the at least one toroidal injection manifold comprises an outer toroidal injection manifold extending about an outer circumference of the premixer and configured to inject the gas fuel or the liquid fuel radially inward about the inlet end of the premixer. 19. The system of claim 12, wherein the at least one toroidal injection manifold comprises an inner toroidal injection manifold extending about an inner circumference of the premixer and configured to inject the gas fuel or the liquid fuel radially outward about the inlet end of the premixer. 20. The system of claim 12, wherein the at least one toroidal injection manifold comprises an inner toroidal injection manifold and an outer toroidal injection manifold, and wherein a fuel split ratio between the inner toroidal injection manifold and the outer toroidal injection manifold is 4 to 1.