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An apparatus is disclosed including a main fuel supply fluidly coupled to a main fuel valve and an arcuate fuel passage receiving main fuel through the main fuel valve. The arcuate fuel passage includes a passage diameter and a radius of curvature which provides sufficient rotational acceleration to

An apparatus is disclosed including a main fuel supply fluidly coupled to a main fuel valve and an arcuate fuel passage receiving main fuel through the main fuel valve. The arcuate fuel passage includes a passage diameter and a radius of curvature which provides sufficient rotational acceleration to the main fuel such that a liquid portion of the main fuel is deposited on an outer wall of the arcuate fuel passage. The apparatus includes a fuel injector nozzle that receives the main fuel from the arcuate fuel passage, and injects the main fuel into a combustion chamber for a turbine engine. The apparatus further includes a pilot fuel supply fluidly coupled to a pilot fuel passage and a fuel selector structured to selectively provide the main fuel or the pilot fuel to the fuel injector nozzle.

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1. An apparatus, comprising: a main fuel supply fluidly coupled to a main fuel valve;an arcuate fuel passage receiving main fuel through the main fuel valve, wherein the arcuate fuel passage comprises a passage diameter and a radius of curvature structured to provide sufficient rotational accelerati

1. An apparatus, comprising: a main fuel supply fluidly coupled to a main fuel valve;an arcuate fuel passage receiving main fuel through the main fuel valve, wherein the arcuate fuel passage comprises a passage diameter and a radius of curvature structured to provide sufficient rotational acceleration to the main fuel such that a liquid portion of the main fuel is deposited on an outer wall of the arcuate fuel passage; anda fuel injector nozzle structured to receive the main fuel from the arcuate fuel passage, and to inject the main fuel into a combustion chamber for a turbine engine;wherein the main fuel valve is structured to maintain a backpressure on the main fuel supply such that fuel in the main fuel supply is a liquid phase. 2. The apparatus of claim 1, wherein the arcuate fuel passage comprises a helical fuel passage and wherein the radius of curvature is defined by a helix diameter. 3. The apparatus of claim 2, further comprising: a pilot fuel supply fluidly coupled to a pilot fuel passage; anda fuel selector structured to selectively provide the main fuel or the pilot fuel to the fuel injector nozzle. 4. The apparatus of claim 3, further comprising a controller structured to determine a fuel phase value and to command the fuel selector to provide the main fuel to the fuel injector nozzle in response to a determination that the fuel phase value is a phase value selected from the list of phases consisting of a vapor phase, a supercritical fluid phase, and a mixed vapor-liquid phase. 5. The apparatus of claim 4, wherein the controller is further structured to determine the fuel phase value as an estimated fuel phase at operating conditions present in the fuel injector nozzle. 6. The apparatus of claim 4, wherein the controller is further structured to determine the fuel phase value in response to at least one parameter selected from the parameters consisting of a main fuel supply temperature, a main fuel supply pressure, a pilot fuel supply temperature, a pilot fuel supply pressure, an injection chamber temperature, and an injection chamber pressure. 7. The apparatus of claim 3, further comprising a controller structured to command the fuel selector to provide the pilot fuel to the fuel injector nozzle in response to at least one selection scheme selected from the schemes consisting of: determining the turbine engine is in a startup operating period;determining a temperature is below a threshold value; anddetermining a fuel phase value is a liquid phase. 8. The apparatus of claim 3, further comprising a pilot fuel circuit comprising the pilot fuel supply, the pilot fuel passage, and at least a portion of the fuel injector nozzle, wherein the pilot fuel circuit comprises one of an airblast fuel injector and a piloted airblast fuel nozzle. 9. A method, comprising: determining a fuel delivery rate requirement for a turbine engine;determining a fuel passage diameter in response to the fuel delivery rate requirement;determining a helix diameter in response to the fuel passage diameter and the fuel delivery rate requirement, wherein rotational acceleration experienced by fuel flowing through a helical passage having the fuel passage diameter and the helix diameter is sufficient to deposit a liquid portion of the fuel on an outer wall of the helical passage;providing the helical passage fluidly coupled to a main fuel supply on an upstream side and a fuel injector nozzle at a downstream side;providing a pilot fuel passage fluidly coupled to a pilot fuel supply at an upstream side and fluidly coupled to the fuel injector nozzle at a downstream side;determining a fuel phase value;selectively providing a fuel to a fuel injector nozzle from one of the helical passage or the pilot fuel passage in response to the fuel phase value;selectively providing the fuel from the pilot fuel passage in response to determining a temperature is below a threshold value; andinjecting the fuel into a combustion chamber of the turbine engine. 10. The method of claim 9, further comprising selectively providing fuel from the helical passage to the fuel injector nozzle in response to determining whether the fuel phase value is a phase value selected from the list of phases consisting of a vapor phase, a supercritical fluid phase, and a mixed vapor-liquid phase. 11. The method of claim 9, wherein the determining the fuel phase value comprises estimating a fuel phase at operating conditions present in the fuel injector nozzle. 12. The method of claim 9, further comprising determining the fuel phase value in response to at least one parameter selected from the parameters consisting of a main fuel supply temperature, a main fuel supply pressure, a pilot fuel supply temperature, a pilot fuel supply pressure, an injection chamber temperature, and an injection chamber pressure. 13. The method of claim 9, further comprising selectively providing the fuel from the pilot fuel passage in response to determining the turbine engine is in a startup operating period. 14. The method of claim 9, wherein the fuel from the pilot fuel passage is provided in response to determining the fuel phase value is a liquid phase. 15. The method of claim 14, further comprising maintaining a backpressure on the main fuel supply such that fuel in the main fuel supply is a liquid phase. 16. A computer program product comprising a computer useable medium having a computer readable program, wherein the computer readable program when executed on a computer causes the computer to: estimate a fuel phase at operating conditions present in a fuel injector nozzle of a turbine engine;determine whether a fuel phase value is a phase value selected from the list of phases consisting of a vapor phase, a supercritical fluid phase, and a mixed vapor-liquid phase;provide fuel from a helical passage to the fuel injector nozzle in response to determining whether the fuel phase value is a phase value selected from the list of phases consisting of a vapor phase, a supercritical fluid phase, and a mixed vapor-liquid phase;provide fuel from a pilot fuel passage to the fuel injector nozzle in response to at least one selection scheme selected from the schemes consisting of: determining the turbine engine is in a startup operating period;determining a temperature is below a threshold value; anddetermining the fuel phase value is a liquid phase; andwherein the helical fuel passage comprises a passage diameter and a helix diameter structured to provide sufficient rotational acceleration to a main fuel such that a liquid portion of the main fuel is deposited on an outer wall of the helical fuel passage. 17. The computer program product of claim 16, wherein the computer readable program when executed on the computer further causes the computer to estimate the fuel phase in response to at least one parameter selected from the parameters consisting of a main fuel supply temperature, a main fuel supply pressure, a pilot fuel supply temperature, a pilot fuel supply pressure, an injection chamber temperature, and an injection chamber pressure. 18. The computer program product of claim 16, wherein the computer readable program when executed on the computer further causes the computer to command a main fuel supply valve to maintain a backpressure on the main fuel supply such that fuel in the main fuel supply is a liquid phase. 19. A method, comprising: determining a fuel delivery rate requirement for a turbine engine;determining a fuel passage diameter in response to the fuel delivery rate requirement;determining a helix diameter in response to the fuel passage diameter and the fuel delivery rate requirement, wherein rotational acceleration experienced by fuel flowing through a helical passage having the fuel passage diameter and the helix diameter is sufficient to deposit a liquid portion of the fuel on an outer wall of the helical passage;providing the helical passage fluidly coupled to a main fuel supply on an upstream side and a fuel injector nozzle at a downstream side;providing a pilot fuel passage fluidly coupled to a pilot fuel supply at an upstream side and fluidly coupled to the fuel injector nozzle at a downstream side;determining a fuel phase value;selectively providing a fuel to a fuel injector nozzle from one of the helical passage or the pilot fuel passage in response to the fuel phase value;selectively providing the fuel from the pilot fuel passage in response to determining the fuel phase value is a liquid phase; andinjecting the fuel into a combustion chamber of the turbine engine. 20. A method, comprising: determining a fuel delivery rate requirement for a turbine engine;determining a fuel passage diameter in response to the fuel delivery rate requirement;determining a helix diameter in response to the fuel passage diameter and the fuel delivery rate requirement, wherein rotational acceleration experienced by fuel flowing through a helical passage having the fuel passage diameter and the helix diameter is sufficient to deposit a liquid portion of the fuel on an outer wall of the helical passage;providing the helical passage fluidly coupled to a main fuel supply on an upstream side and a fuel injector nozzle at a downstream side;maintaining a backpressure on the main fuel supply such that fuel in the main fuel supply is a liquid phase;providing a pilot fuel passage fluidly coupled to a pilot fuel supply at an upstream side and fluidly coupled to the fuel injector nozzle at a downstream side;determining a fuel phase value;selectively providing a fuel to a fuel injector nozzle from one of the helical passage or the pilot fuel passage in response to the fuel phase value; andinjecting the fuel into a combustion chamber of the turbine engine. 21. A computer program product comprising a computer useable medium having a computer readable program, wherein the computer readable program when executed on a computer causes the computer to: estimate a fuel phase at operating conditions present in a fuel injector nozzle of a turbine engine;determine whether a fuel phase value is a phase value selected from the list of phases consisting of a vapor phase, a supercritical fluid phase, and a mixed vapor-liquid phase;provide fuel from a helical passage to the fuel injector nozzle in response to determining whether the fuel phase value is a phase value selected from the list of phases consisting of a vapor phase, a supercritical fluid phase, and a mixed vapor-liquid phase;wherein the helical fuel passage comprises a passage diameter and a helix diameter structured to provide sufficient rotational acceleration to a main fuel such that a liquid portion of the main fuel is deposited on an outer wall of the helical fuel passage; andcommand a main fuel supply valve to maintain a backpressure on the main fuel supply such that fuel in the main fuel supply is a liquid phase.