A fuel injector and turbine engine incorporating the fuel injector are provided. The fuel injector includes an active cooling system that insulates fuel flowing through the fuel injector from heat energy within the turbine engine. The cooling system includes a cooling air passage that includes an in
A fuel injector and turbine engine incorporating the fuel injector are provided. The fuel injector includes an active cooling system that insulates fuel flowing through the fuel injector from heat energy within the turbine engine. The cooling system includes a cooling air passage that includes an inlet and an outlet. The inlet and outlet are in fluid communication with the interior of an engine case of the turbine engine. The inlet is at a higher air pressure location than the outlet such that air is siphoned through the cooling air passage. A portion of the cooling air passage includes a heat exchanger for extracting heat energy from the cooling air. The cooling air passes through the fuel injector after it has passed through the heat exchanger. The heat exchanger is positioned external to the engine case and in thermal communication with the ambient.
대표청구항▼
What is claimed is: 1. A fuel injector for use in a gas turbine engine having an engine case housed within a nacelle, the engine case including therein a compressor for compressing atmospheric air to form high pressure and high temperature compressed air that flows into a compressor discharge area
What is claimed is: 1. A fuel injector for use in a gas turbine engine having an engine case housed within a nacelle, the engine case including therein a compressor for compressing atmospheric air to form high pressure and high temperature compressed air that flows into a compressor discharge area upstream of and for use by a combustor also housed in the engine case, the nacelle forming a nacelle air bypass flow path around the engine case to allow low temperature nacelle air to flow therethrough, the fuel injector comprising: a central body defining a fuel flow passage extending between a fuel inlet and a fuel outlet; a cooling system including at least one orifice that defined a cooling air passage extending between an orifice cooling air inlet located in the compressor discharge area and a cooling air outlet located in the combustor; at least a portion of the cooling air passage extending through the engine case and into the nacelle air bypass flow path around the engine case, the cooling air passage thereafter extending through the central body and in thermal communication with the central body. 2. The fuel injector of claim 1, wherein the central body includes a support structure surrounded by a heat shield forming a gap therebetween, the gap forming a portion of the cooling air passage. 3. The fuel injector of claim 1, further including a mounting structure for mounting the fuel injector to an engine case, the orifice cooling air inlet and cooling air outlet being positioned relative to the mounting structure such that the orifice cooling air inlet and cooling air outlet are both positioned within the engine case when the fuel injector is mounted thereto. 4. The fuel injector of claim 1, wherein the cooling system includes a heat exchanger forming a portion of the cooling air passage that extends into the nacelle air bypass flow path around the engine case and that is interposed between the cooling air inlet and cooling air outlet. 5. The fuel injector of claim 4, wherein the central body includes a mounting structure for mounting the fuel injector to an engine case, the heat exchanger being positioned relative to the mounting structure such that the heat exchanger is positioned external to the engine case in the nacelle air bypass flow path when the fuel injector is mounted thereto. 6. The fuel injector of claim 1, wherein the fuel outlet and cooling air outlet are positioned adjacent one another. 7. The fuel injector of claim 6, further including an atomizer, the cooling air outlet and fuel outlet formed by the atomizer. 8. The fuel injector of claim 7, wherein the central body includes a mounting structure for mounting the fuel injector to the engine case, the mounting structure being proximate an upstream end of the fuel injector while the atomizer is proximate a downstream end of the fuel injector. 9. The fuel injector of claim 5, wherein the orifice cooling air inlet and cooling air outlet are positioned relative to the mounting structure such that the orifice cooling air inlet and cooling air outlet are both positioned within the engine case when the fuel injector is mounted thereto. 10. The fuel injector of claim 9, wherein a portion of the cooling air passage between the orifice cooling air inlet and the heat exchanger passes through the mounting structure. 11. The fuel injector of claim 3, wherein the mounting structure is a radially outward extending flange including a first face facing an upstream end of the fuel injector and a second face facing a downstream end of the fuel injector, the second face facing the orifice cooling air inlet and cooling air outlet. 12. A turbine engine comprising: an engine case; a nacelle positioned around the engine case forming a nacelle air bypass flow path therebetween to allow low temperature nacelle air to flow therethrough; a compressor within the engine case; a compressor discharge area downstream of the compressor in which compressed air from the compressor is discharged at high pressure and high temperature; a combustor within the engine case and positioned downstream from the compressor and the compressor discharge area, the combustor in fluid communication with the compressor discharge area through a combustor boundary wall, the combustor boundary wall creating a pressure differential between the combustor discharge area and the combustor such that the combustor is at a lower pressure than the compressor discharge area; a fuel injector mounted within to the engine case, the fuel injector including a central body defining a fuel flow path having a fuel outlet within the combustor; and a cooling system including at least one orifice that defined a cooling air passage, passing through and in thermal communication with the central body, the cooling air passage including an orifice cooling air inlet in the compressor discharge area for receiving the high pressure and high temperature compressed air from the compressor and a cooling air outlet in the combustor downstream of the combustor boundary wall, at least one portion of the cooling air passage interposed between the orifice cooling air inlet and cooling air outlet being external to the engine case and extending into the nacelle air bypass flow path in thermal communication with the low temperature nacelle air. 13. The turbine engine of claim 12, wherein the at least one portion of the cooling air passage is in thermal communication with the low temperature nacelle air external to the engine case flowing in the nacelle air bypass flow path for transferring heat energy to the low temperature nacelle air from high pressure and high temperature compressed air entering the orifice cooling air inlet from the compressor discharge area and exiting the cooling air outlet into the combustor downstream of the combustor boundary wall. 14. The turbine engine of claim 13, wherein the fuel injector further includes a heat shield surrounding, at least in part, the central body forming a gap therebetween, the gap forming a part of the cooling air passage. 15. The turbine engine of claim 12, wherein the engine case includes an aperture through which the central body extends, the fuel injector further including a mounting structure for securing the fuel injector within the aperture and to the engine case, a portion of the cooling air passage between the orifice cooling air inlet and the portion that is external to the engine case passing through the mounting structure for securing the fuel injector to the engine case. 16. The turbine engine of claim 15, wherein the mounting structure is a radially outward extending mounting flange that extends outward from the central body that overlaps a portion of an outer surface of the engine case. 17. The turbine engine of claim 12, further including a fuel supply path operably coupled to the fuel injector, the fuel supply path including a heat exchanger for transferring heat energy from fuel passing through the fuel supply path to the ambient. 18. The fuel injector of claim 1, wherein the high pressure and high temperature compressed air from the compressor is actively drawn into the orifice cooling air inlet by a pressure differential between the compressor discharge area in which the orifice cooling air inlet is located and the combustor in which the cooling air outlet is located. 19. The fuel injector of claim 4, wherein the high pressure and high temperature compressed air from the compressor is cooled by the low temperature nacelle air prior to flowing through the central body such that cooling of the fuel flowing through the fuel flow passage. 20. The turbine engine of claim 12, wherein the high pressure and high temperature compressed air from the compressor is actively drawn into the cooling air inlet by a pressure differential between the compressor discharge area in which the orifice cooling air inlet is located and the combustor in which the cooling air outlet is located.
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