초록

An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct.

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1. An assembly for a gas turbine engine, the assembly comprising: an intermediate case defining an annular transition duct;an accessory gearbox integrally formed with the annular transition duct, wherein the accessory gearbox comprises a plurality of lobes, wherein the plurality of lobes are integra

1. An assembly for a gas turbine engine, the assembly comprising: an intermediate case defining an annular transition duct;an accessory gearbox integrally formed with the annular transition duct, wherein the accessory gearbox comprises a plurality of lobes, wherein the plurality of lobes are integrally formed with the accessory gearbox, and wherein each of the plurality of lobes is configured to receive at least one accessory. 2. The assembly of claim 1, wherein the annular transition duct has a shared wall with the gearbox, the shared wall defining an outer diameter boundary of a flowpath through the annular transition duct. 3. The assembly of claim 1, wherein each of the plurality of lobes are divided from each other by a side wall, the side wall extending from the annular transition duct substantially in a plane that extends in axial and radial directions relative to an engine centerline. 4. The assembly of claim 2, wherein the shared wall has a substantially frusto-conical shape. 5. The assembly of claim 1, wherein the gearbox has a detachable portion. 6. The assembly of claim 5, wherein the detachable portion comprises a cover, and wherein an interface between the cover and another portion of the gearbox is sealed with a gasket. 7. The assembly of claim 1, wherein each of the plurality of lobes comprises: a first side wall extending from the annular transition duct substantially in a first plane that extends in axial and radial directions relative to an engine centerline;a second side wall extending from the annular transition duct substantially in a second plane that extends in axial and radial directions relative to an engine centerline;a front wall extending from the annular transition duct substantially in a third plane that extends in angular and radial directions relative to an engine centerline;an aft wall extending from the annular transition duct substantially in a fourth plane that extends in angular and radial directions relative to an engine centerline; andan outer wall, connected to the first side wall, the second side wall, the front wall, and the aft wall, wherein the first side wall shares an edge with the front wall, which shares an edge with the second side wall, which shares an edge with the back wall, which shares an edge with the first side wall. 8. The assembly of claim 1, wherein the gearbox comprises a connection passage between the plurality of lobes. 9. An assembly for a gas turbine engine, the assembly comprising: an intermediate case defining a transition duct;an accessory gearbox having a shared wall with the transition duct, wherein the gearbox comprises a first lobe and a second lobe, wherein at least one accessory is mounted on each lobe;a first tower shaft powered by the gas turbine engine for providing rotational force input to at least one gear positioned in the first lobe; anda second tower shaft powered by the gas turbine engine for providing rotational force input to at least one gear positioned in the second lobe. 10. The assembly of claim 9, wherein the gearbox, the shared wall, and the transition duct are integrally formed. 11. The assembly of claim 9, wherein the first lobe and the second lobe are connected together in fluid communication by a connection passage. 12. The assembly of claim 11, wherein the connection passage is integrally formed with the first lobe and the second lobe. 13. The assembly of claim 11, wherein the connection passage is configured to transfer a fluid from the first lobe to the second lobe utilizing gravitational force. 14. The assembly of claim 9, wherein the first lobe is divided from the second lobe by a side wall, the side wall extending from the annular transition duct substantially in a plane that extends in axial and radial directions relative to an engine centerline. 15. The assembly of claim 9, wherein the first lobe defines a mounting space for mounting an elongated accessory in a substantially vertical position. 16. The assembly of claim 9, wherein the second lobe is located substantially at a bottom dead center position of the gas turbine engine relative to an engine centerline. 17. The assembly of claim 9, wherein the second lobe is angularly spaced from the first lobe about the engine centerline. 18. The assembly of claim 9, wherein the first lobe comprises: a first side wall extending from the annular transition duct substantially in a first plane that extends in axial and radial directions relative to an engine centerline;a second side wall extending from the annular transition duct substantially in a second plane that extends in axial and radial directions relative to an engine centerline;a front wall extending from the annular transition duct substantially in a third plane that extends in angular and radial directions relative to an engine centerline;an aft wall extending from the annular transition duct substantially in a fourth plane that extends in angular and radial directions relative to an engine centerline; andan outer wall, connected to the first side wall, the second side wall, the front wall, and the aft wall, wherein the first side wall shares an edge with the front wall, which shares an edge with the second side wall, which shares an edge with the back wall, which shares an edge with the first side wall. 19. A method for housing gearing in a gas turbine engine, comprising steps of: providing an intermediate case that includes an accessory gearbox and a transition duct with a shared wall between the accessory gearbox and the transition duct; andmounting at least one accessory on each of a plurality of lobes of the accessory gearbox. 20. The method of claim 19, wherein mounting at least one accessory includes: mounting a first group of accessories each driven as a function of a first rotational input to a first lobe; andmounting a second group of accessories each driven as a function of a second rotational input to a second lobe. 21. The method of claim 19, comprising a further step of: linking a first lobe fluidically to a second lobe via a connection passage. 22. The method of claim 21, comprising a further step of: collecting fluid in the second lobe that has drained from the first lobe through the connection passage by way of gravity. 23. The method of claim 19, comprising a further step of: integrally casting a first lobe and a second lobe with the transition duct.