A gas turbine engine fuel delivery system which includes an external fuel manifold fastened to the outer surface of a casing surrounding the combustor of the engine and which includes a plurality of inlet manifold tubes circumferentially disposed in serial flow communication. A plurality of fuel noz
A gas turbine engine fuel delivery system which includes an external fuel manifold fastened to the outer surface of a casing surrounding the combustor of the engine and which includes a plurality of inlet manifold tubes circumferentially disposed in serial flow communication. A plurality of fuel nozzles are mounted to the casing and are axially spaced apart from the fuel manifold on the outer surface of the casing. A plurality of jumper tubes are disposed outside the casing and feed fuel flow from the fuel manifold to the fuel nozzles. The jumper tubes have a rigidity that is less than that of the inlet manifold tubes of the fuel manifold such that the jumper tubes elastically deflect under load.
대표청구항▼
1. A fuel delivery system for a gas turbine engine having a combustor, a multistage compressor and a multistage turbine in serial flow communication within a surrounding core engine casing, the fuel delivery system comprising: an external fuel manifold disposed outside the core engine casing forward
1. A fuel delivery system for a gas turbine engine having a combustor, a multistage compressor and a multistage turbine in serial flow communication within a surrounding core engine casing, the fuel delivery system comprising: an external fuel manifold disposed outside the core engine casing forward of the multistage turbine of the gas turbine engine, the external fuel manifold extending circumferentially around the casing and comprising a plurality of inlet manifold tubes circumferentially disposed in serial flow communication, each of the inlet manifold tubes being interconnected to a next circumferentially adjacent inlet manifold tube by a fixed manifold adapter directly fastened to an outer surface of the core engine casing at a first axial position;a plurality of circumferentially spaced apart fuel nozzles, the fuel nozzles having a radially outer end mounted to the core engine casing at a second axial position offset from the first axial position such that the fuel nozzles are axially spaced apart from the external fuel manifold on the outer surface of the core engine casing; anda plurality of jumper tubes disposed outside the core engine casing and interconnecting the fixed manifold adapters and radially outer ends of the fuel nozzles disposed outside the core engine casing, the jumper tubes feeding fuel flow from the external fuel manifold to the fuel nozzles, the jumper tubes having a rigidity that is less than that of the inlet manifold tubes of the external fuel manifold such that the jumper tubes elastically deflect under load. 2. The fuel delivery system as defined in claim 1, wherein the jumper tubes have a hairpin-like shape. 3. The fuel delivery system as defined in claim 1, wherein each of said inlet manifold tubes of the external fuel manifold feeds at least two fuel nozzles via said jumper tubes. 4. The fuel delivery system as defined in claim 1, wherein the jumper tubes elastically deflect more than the inlet manifold tubes of the external fuel manifold. 5. The fuel delivery system as defined in claim 1, wherein the jumper tubes have at least one of a shape, wall thickness and material which enables the jumper tubes to be more flexible than the inlet manifold tubes of the external fuel manifold. 6. The fuel delivery system as defined in claim 1, wherein the jumper tubes feed fuel flow from the external fuel manifold to radially projecting outer heads of the fuel nozzles disposed outside the casing. 7. The fuel delivery system as defined in claim 1, wherein each manifold adapter has two jumper tubes connected thereto, each of the two jumper tubes feeding fuel to a separate one of the fuel nozzles. 8. The fuel delivery system as defined in claim 1, wherein each of the jumper tubes has an upstream end detachably connected to the external fuel manifold and a downstream end detachably connected to one of the fuel nozzles such as to permit removal of the jumper tube while the external fuel manifold remains fastened in place on the casing. 9. The fuel delivery system as defined in claim 8, wherein the fuel nozzles are removably mounted to the casing, such that individual removal of the one of the fuel nozzles is enabled, following removal of the jumper tube, while the external fuel manifold remains fastened in place on the casing. 10. The fuel delivery system as defined in claim 1, wherein each said manifold adapter is fastened to the casing by attachment mounts including a boss disposed on the outer surface of the casing and a mating threaded fastener which engages the boss to fasten the external fuel manifold to the casing. 11. A gas turbine engine including a multi-stage compressor, a combustor and a multi-stage turbine in serial flow communication, the gas turbine engine comprising: a core engine casing enclosing the multi-stage compressor, the combustor and the multi-stage turbine;an external fuel manifold disposed outside the core engine casing, the external fuel manifold being disposed forward of the multistage turbine, the external fuel manifold including a plurality of inlet manifold tubes interconnected by fixed manifold adapters, the fixed manifold adapters being directly fastened to an outer surface of the core engine casing;a plurality of circumferentially distributed fuel nozzles fastened to the core engine casing and each having a radially outer end thereof which is disposed outside the core engine casing and axially spaced apart from the external fuel manifold such that the radially outer ends of the fuel nozzles are axially offset from the fixed manifold adapters the external fuel manifold on the outside of the core engine casing; anda plurality of jumper tubes disposed outside the core engine casing and interconnecting in fuel flow communication the radially outer ends of the fuel nozzles and the fixed manifold adapters of the external fuel manifold, both of which are disposed outside the core engine casing and fixed thereto, the jumper tubes having a flexibility that is greater than that of the external fuel manifold such that the fuel nozzles bear substantially none of the load imposed on the core engine casing by the weight of the external fuel manifold. 12. The gas turbine engine as defined in claim 11, wherein the external fuel manifold is substantially more rigid than the jumper tubes. 13. The gas turbine engine as defined in claim 11, wherein the external fuel manifold includes a plurality of inlet manifold tubes circumferentially disposed in serial flow communication, each of the inlet manifold tubes being interconnected to a next circumferentially adjacent inlet manifold tube by a manifold adapter. 14. The gas turbine engine as defined in claim 13, wherein each of the inlet manifold tubes feeds two of the fuel nozzles via two jumper tubes, the two jumper tubes being connected to one of the manifold adaptors. 15. The gas turbine engine as defined in claim 11, wherein each of the jumper tubes has an upstream end detachably connected to the external fuel manifold and a downstream end detachably connected to one of the fuel nozzles, such as to permit removal of the jumper tubes while the external fuel manifold remains fastened in place on the casing. 16. The gas turbine engine as defined in claim 15, wherein the fuel nozzles are removably mounted to the casing, and an individual one of the fuel nozzles is removable from the casing while the external fuel manifold remains fastened in place on the casing.
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이 특허에 인용된 특허 (15)
Zaremba Henry V. (Tempe AZ) Lucas Lonnie J. (Chandler AZ) Catmull Paul B. (Gilbert AZ) McAdams Maynard L. (Chandler AZ) Johnson Karl P. (Tempe AZ), Apparatus for use in a fuel delivery system for a gas turbine engine.
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