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A fuel injector (36) for alternate fuels (26A, 26B) with different energy densities. Vanes (47B) extend radially from a fuel delivery tube structure (20B) with first and second fuel supply channels (19A, 19B). Each vane has first and second radial passages (21A, 21B) communicating with the respectiv

A fuel injector (36) for alternate fuels (26A, 26B) with different energy densities. Vanes (47B) extend radially from a fuel delivery tube structure (20B) with first and second fuel supply channels (19A, 19B). Each vane has first and second radial passages (21A, 21B) communicating with the respective fuel supply channels, and first and second sets of apertures (23A, 23B). The first fuel supply channel, first radial passage, and first apertures form a first fuel delivery pathway providing a first fuel flow rate at a given fuel delivery pathway backpressure that is essentially common to both sets of fuel delivery pathway apertures. The second fuel supply channel, second radial passage, and second apertures form a second fuel delivery pathway providing a second fuel flow rate that may be at least 1 about twice the first fuel flow rate at the given fuel delivery pathway backpressure.

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1. A gas turbine fuel injector for alternate fuels of different energy densities, comprising: first and second main fuel delivery pathways through a main fuel delivery tube structure, through vanes extending radially therefrom, and exiting through respective first and second sets of apertures in ext

1. A gas turbine fuel injector for alternate fuels of different energy densities, comprising: first and second main fuel delivery pathways through a main fuel delivery tube structure, through vanes extending radially therefrom, and exiting through respective first and second sets of apertures in exterior surfaces of the vanes, wherein each fuel delivery pathway is configured to independently supply a quantity of fuel sufficient to enable injector operation, and wherein only one fuel delivery pathway is necessary for injector operation;wherein the first main fuel delivery pathway provides a first main fuel flow rate of a first fuel at a given fuel delivery pathway backpressure that is essentially common to both sets of fuel delivery pathway apertures, and the second main fuel delivery pathway provides a second main fuel flow rate of a second fuel that is at least about twice the first main fuel flow rate at the given fuel delivery pathway backpressure due to a lower pressure loss in the second main fuel delivery pathway from greater cross-sectional areas in respective portions of the second main fuel delivery pathway compared to the first main fuel delivery pathways, wherein the second fuel has a lower energy density than the first fuel andwherein within the vanes the second main fuel delivery pathway comprises a radially extending passage comprising a maximum width not greater than a maximum width of a radial extending passage of the first main fuel delivery pathway. 2. The gas turbine fuel injector of claim 1, comprising: first and a second main fuel supply channels in the main fuel delivery tube structure that alternately supply a respective first main fuel and a second main fuel;a first radial passage in each of a first grouping of the vanes, communicating with the first main fuel supply channel;a second radial passage in each of a second grouping of the vanes, communicating with the second main fuel supply channel;the first set of apertures open between the first radial passage and the exterior surface of said each vane of the first grouping of vanes;the second set of apertures open between the second radial passage and the exterior surface of said each vane of the second grouping of vanes;the first main fuel supply channel, the first radial passages, and the first set of apertures forming the first main fuel delivery pathway; andthe second main fuel supply channel, the second radial passages, and the second set of apertures forming the second main fuel delivery pathway. 3. The fuel injector of claim 2, wherein a same set of vanes comprises the first and second groupings of vanes, wherein each vane of the same set includes at least one of the first radial passages and at least one of the second radial passages. 4. The fuel injector of claim 3, wherein each vane of the same set comprises a front portion and a back portion, the front portion is substantially aligned with a flow direction of a combustion intake air supply, the pack portion is angled relative to the flow direction of the combustion intake air supply, and the first and second radial passages are in the front portion of the vane. 5. The fuel injector of claim 4, wherein some apertures of the second set of apertures open on a pressure side of the vane, and some apertures of the second set of apertures open on a suction side of the vane. 6. The fuel injector of claim 3, further comprising a rounded or gradual transition area between the second main fuel supply channel and each of the second radial passages, wherein the rounded or gradual transition area reduces turbulence in a second main fuel flow in the second radial passages at the given backpressure relative to turbulence in a first main fuel flow in the first radial passages at the given backpressure. 7. The fuel injector of claim 6, wherein the second main fuel delivery pathway further comprises: a third radial passage in each vane of the same set, the second and third radial passages both communicating with the second main fuel supply channel;wherein the rounded or gradual transition area comprises an enlarged and rounded common volume of proximal ends of the second and third radial passages; andwherein a partition between the second and third radial passages has a proximal end that starts radially outwardly from the second main fuel supply channel, thus forming an equalization plenum that reduces an upstream/downstream main fuel pressure differential at the proximal ends of the second and third radial passages. 8. The fuel injector of claim 2, wherein each vane of the first grouping of vanes comprises a trailing edge that is angled relative to a flow direction of an intake air supply, and each vane of the second grouping of vanes is positioned directly upstream of a respective vane of the first grouping of vanes. 9. The fuel injector of claim 1 installed in a gas turbine combustor, wherein the combustor further comprises: a pilot fuel delivery tube structure;first and second pilot fuel supply channels in the pilot fuel delivery tube structure that alternately supply respective first and second pilot fuels;a pilot fuel diffusion nozzle on an end of the pilot fuel delivery tube structure;a first set of pilot fuel diffusion ports in the pilot fuel diffusion nozzle communicating with the first pilot fuel supply channel;a second set of pilot fuel diffusion ports in the pilot fuel diffusion nozzle communicating with the second pilot fuel supply channel;wherein the first pilot fuel supply channel and the first set of pilot fuel diffusion ports provide a first pilot fuel flow rate at a given pilot fuel supply channel backpressure that is essentially common to both sets of diffusion ports; andwherein the second pilot fuel supply channel and the second set of pilot fuel diffusion ports provide a second pilot fuel flow rate that is at least about twice the first pilot fuel flow rate at the given pilot fuel supply channel backpressure. 10. The fuel injector of claim 1, wherein: the delivery tube structure comprises coaxial cylindrical inner and outer tubes, forming an annular first main fuel supply channel between the inner and outer tubes, and providing a second main fuel supply channel in the inner tube;the first main fuel delivery pathway comprises a first radial passage in the vanes communicating with the first main fuel supply channel;the second main fuel delivery pathway comprises second and third radial passages in the vanes communicating with the second main fuel supply channel:the first radial passage is upstream of the second and third radial passages; anda partition between the second and third radial passages has a proximal end that starts radially outwardly from the second main fuel supply channel, thus forming an equalization plenum that reduces an upstream/downstream main fuel pressure differential at proximal ends of the second and third radial passages. 11. A gas turbine fuel injector for alternate fuels of different energy densities, comprising: a plurality of vanes extending radially from a main fuel delivery tube structure;first and second main fuel supply channels in the main fuel delivery tube structure that alternately supply a respective first main fuel and a second main fuel, wherein the second main fuel has a lower energy density than the first main fuel;a first radial passage in each of a first grouping of the vanes, communicating with the first main fuel supply channel;a second radial passage in each of a second grouping of the vanes, communicating with the second main fuel supply channel;a first set of apertures open between the first radial passage and an exterior surface of said each vane of the first grouping of vanes;a second set of apertures open between the second radial passage and an exterior surface of said each vane of the second grouping of vanes;the first main fuel supply channel, the first radial passages, and the first sets of apertures forming a first main fuel delivery pathway having a first main fuel flow rate at a given fuel supply channel backpressure that is essentially common to both sets of apertures;the second main fuel supply channel, the second radial passages, and the second sets of apertures forming a second main fuel delivery pathway having a second main fuel flow rate that differs from the first main fuel flow rate by at least about a factor of two at the given fuel supply channel backpressure,wherein the injector is operable on either fuel delivery pathway; andwherein within the second grouping of the vanes the second radial passage comprising a maximum width not greater than a maximum width of the first radial passage. 12. The fuel injector of claim 11, wherein a same set of vanes comprises the first and second grouping of vanes, wherein each vane of the same set includes at least one of the first radial passages and at least one of the second radial passages. 13. The fuel injector of claim 12, wherein each vane of the same set comprises a front portion and a back portion, the front portion is substantially aligned with a flow direction of an intake air supply, the back portion is angled relative to me flow direction of the intake air supply, and the first and second radial passages are in the front portion of the vane. 14. The fuel injector of claim 13, wherein some apertures of the second set of apertures open on a pressure side of the vane, and some apertures of the second set of apertures open on a suction side of the vane. 15. The fuel injector of claim 12, wherein the second flow rate is at least twice the first flow rate at the given fuel supply channel backpressure due to greater cross-sectional areas in respective portions of the second main fuel delivery pathway compared to the first main fuel delivery pathway. 16. The fuel injector of claim 15, further comprising a rounded or gradual transition area between the second main fuel supply channel and each of the second radial passages, wherein the rounded or gradual transition area reduces turbulence in a second main fuel flow in the second radial passages at th6 given fuel supply channel backpressure relative to turbulence in a first main fuel flow in the first radial passages at the given fuel supply channel backpressure. 17. The fuel injector of claim 16, wherein the second main fuel delivery pathway further comprises: a third radial passage in each vane of the same set, the second and third radial passages both communicating with me second main fuel supply channel;wherein the rounded or gradual transition area comprises an enlarged and rounded common volume of proximal ends of the second and third radial passages; andwherein a partition between the second and third radial passages has a proximal end that starts radially outwardly from the second main fuel supply channel, thus forming an equalization plenum that reduces an upstream/downstream main fuel pressure differential at me proximal ends of the second and third radial passages. 18. The fuel injector of claim 11, wherein the first grouping of vanes each comprise a trailing edge that is angled relative to a flow direction of a combustion intake air supply, and each vane of the second grouping is positioned directly upstream of a respective vane of the first set of vanes. 19. The fuel injector of claim 11 installed in a gas turbine combustor, wherein the combustor further comprises: a pilot fuel delivery tube structure;first and second pilot fuel supply channels in the pilot fuel delivery tube structure that alternately supply the respective first main fuel and the second main fuel as respective first and second pilot fuels;a pilot fuel diffusion nozzle on an end of the pilot fuel delivery tube structure;a first set of pilot fuel diffusion ports in the pilot fuel diffusion nozzle communicating with the first pilot fuel supply channel;a second set of pilot fuel diffusion ports in the pilot fuel diffusion nozzle communicating with the second pilot fuel supply channel;wherein the first pilot fuel supply channel and the first set of pilot fuel diffusion ports provides a first pilot fuel flow rate at a given pilot fuel supply channel backpressure that is essentially common to both sets of diffusion ports;wherein the second pilot fuel supply channel and the second set of pilot fuel diffusion ports provides a second pilot fuel flow rate that differs from the first pilot fuel flow rate by at least about a factor of two at the given pilot fuel supply channel backpressure. 20. A gas turbine fuel injector for alternate fuels, comprising a plurality of vanes extending radially from a fuel delivery tube structure;a first and a second fuel supply channel in the fuel delivery tube structure;a first and a second radial passage in each vane, the first and second radial passage communicating with the respective fuel supply channel;first and second sets of apertures between the respective radial passage and an exterior surface of the vane;the first fuel supply channel, the first radial passage, and the first set of apertures forming a first fuel delivery pathway that provides a first fuel flow rate at a given difference between a first fuel supply channel inlet pressure and a backpressure proximate the first set of apertures;the second fuel supply channel, the second radial passage, and the second set of apertures forming a second fuel delivery pathway that provides a second fuel flow rate of at least twice the first fuel flow rate at the given pressure difference;wherein the difference between the first and second fuel flow rates is achieved by different cross-sectional areas in respective portions of the first and second fuel delivery pathways and by a rounded transition area between the second fuel supply channel and each of the second radial passages; andwherein a first fuel is supplied to the first fuel supply channel and alternately, a second fuel having about half or less energy density of the first fuel is supplied to the second fuel supply channel, andwherein each fuel delivery pathway is configured to independently supply a quantity of fuel sufficient to enable injector operation, and wherein only one fuel delivery pathway is necessary for injector operation; andwherein a perimeter of a largest cross section of the second radial passage is substantially aligned with a perimeter of the first radial passage with respect to a flow direction of compressed air flowing thereby.