Ge Avio S.r.l.

General Electric Company

Davide Lauria

Juraj Hrubec

Marco Garabello

Paolo Altamura

Simone Castellani

Alessio Gargioli

Gian Mario Bragallini

Steven Edward Nolte

Michael John Murray

Bojan Lukovic

Christian Michael Fernholz

Rocco Pellettieri

Ivan Golovin

A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.

Turbomachine and gear assembly

A gearbox for an engine includes a rotating element and a turbomachine, the turbomachine includes a shaft, and the rotating element is driven by the shaft across the gearbox. The gearbox includes a ring gear, a first sun gear and a second sun gear each configured to be driven by the shaft of the turbomachine, a first planet gear comprising a first gear portion and a second gear portion, and a second planet gear comprising a first gear portion and a second gear portion.

Gearbox for an engine

An aspect of the present disclosure is directed to a method for mitigating rotor bow in a turbo machine. The method includes rotating a rotor over a first period of time; discontinuing rotation of the rotor for a second period of time; and iterating, over an overall period of time, rotation of the rotor over the first period of time and discontinuing rotation of the rotor for the second period of time.

Method and system for mitigating rotor bow in a turbo machine

The present disclosure is directed to a turbine engine () defining an axial direction, a radial direction, a circumferential direction, a first end () and a second end () opposite of the first end () along the axial direction. The turbine engine includes a propeller assembly () proximate to the first end including a plurality of blades () arranged in the circumferential direction disposed around an axial centerline (), and a feathering mechanism () including a hollow piston rod (). The feathering mechanism rotates the plurality of blades about a pitch axis () extended in the radial direction from the axial centerline. The turbine engine further includes a housing () proximate to the second end disposed in adjacent arrangement with the propeller assembly in the axial direction. The axial centerline is defined through the propeller assembly and the housing. The turbine engine further includes a beta tube assembly () extended through the hollow piston rod and at least partially through the housing in coaxial alignment with the axial centerline. The beta tube assembly defines an at least partially hollow walled pipe () extended along the axial direction. The beta tube assembly further defines a plurality of grooves () extended along the axial direction proximate to the housing. A first groove () extends at least partially in the circumferential direction and along the axial direction to at least partially define a helix () corresponding to a rotatable range of the plurality of blades about the pitch axis, and a second groove () extends in the axial direction.

System and method of locating feathering propeller blade angular position

A system for feathering a propeller assembly disposed within a housing of the propeller assembly has a sleeve defining an outer wall and one or more sleeve tabs extended outward in a radial direction along at least a circumferential portion of the sleeve, wherein the one or more sleeve tabs is separated from the outer wall in an axial direction, a retainer defining one or more retainer tabs extended inward in the radial direction, wherein the one or more retainer tabs is disposed between the outer wall and the one or more sleeve tabs of the sleeve along the axial direction, and a beta tube assembly extended through the sleeve along the axial direction. The beta tube assembly defines one or more internal walls. The one or more internal walls defines a hydraulic fluid transfer cavity in fluid communication with one or more hydraulic fluid transfer orifices.

Transfer bearing collapsing device

Growing community of inventors

Turin, Italy

Davide Lauria