Ge Avio S.r.l.

Pietro Molesini

Fabio De Bellis

Andrea Piazza

Saypen Baraggia Au Yeung

Miriam Manzoni

Alberto Frezet

Alessandro Bordoni

Lorenzo Dal Mas

Rosaria Conte

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-11.0, and a gearbox oil flow rate at an inlet of the gearbox within a range of 5-25 gallons per minute at a max takeoff condition.

Gearbox efficiency rating for turbomachine engines

A lubricant system for supplying lubrication to a component in a turbine engine includes a lubricant reservoir, a supply line fluidly coupling the lubricant reservoir to the component in the turbine engine, a scavenge line fluidly coupling the component to the lubricant reservoir, and a bypass line fluidly coupling the supply line to the scavenge line and bypassing the component.

Lubricant system

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0.

An air/oil separator is provided. The air/oil separator includes an oil manifold having a first air/oil inlet and a second air/oil inlet; a first separation chamber in communication with the first air/oil inlet; and a second separation chamber separate from the first separation chamber, the second separation chamber in communication with the second air/oil inlet.

Air/oil separator apparatus and method

Cooling sub-systems and methods of manufacturing cooling sub-systems are provided. For example, a cooling sub-system comprises a heat exchanger and a manifold that comprises a first sensor seat and a first valve seat, which are in fluid communication with a flow of a working fluid through the heat exchanger and the manifold. The heat exchanger and manifold are integrally formed as a single unit. In some embodiments, the manifold further comprises a second sensor seat, a second valve seat, and a plurality of internal passageways, which fluidly connects the first and second sensor seats and the first and second valve seats a working fluid inlet and a working fluid outlet for an ingress of working fluid into and out of the manifold. The cooling sub-system may be manufactured by one or more additive manufacturing methods.

Integrated cooling sub-system

A gear assembly for an aeronautical engine includes a first gear disposed at a centerline axis of the gear assembly, a second gear coupled to the first gear in adjacent radial arrangement to form a first mesh between the first gear and the second gear, a static portion coupled to the second gear in adjacent circumferential arrangement, the static portion defining a pocket, and a spraybar disposed within the static portion such that a supply opening of the spraybar is directed at the first mesh between the first gear and the second gear. The supply opening provides a flow of lubricant to the first mesh between the first gear and the second gear and at least a portion of the flow of lubricant is collected by the pocket. The flow of lubricant is continuously released from the pocket to the gear system.

Gear assembly for aeronautical engine with lubricant storing pockets

A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.

Turbomachines and epicyclic gear assemblies with lubrication channels

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

A turbomachine engine can include an unducted fan assembly, an unducted vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The unducted fan assembly can include a plurality of fan blades. The unducted vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the unducted fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

A gear assembly for an aeronautical engine that includes a first gear disposed at a centerline axis of the gear assembly; a second gear coupled to the first gear in adjacent radial arrangement to form a first mesh between the first gear and the second gear; a third gear coupled to the second gear in adjacent radial arrangement to form a second mesh between the second gear and the third gear; a collector rotatably coupled with the third gear; and a lubricant input portion disposed between a portion of the first gear and the second gear such that a first supply opening of the lubricant input portion is directed at the first mesh between the first gear and the second gear. The first supply opening provides a flow of lubricant to the first mesh with a portion of the flow of lubricant is collected by the collector.

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Turin, Italy

Pietro Molesini