Ge Avio S.r.l.

General Electric Company

Fiatavio S.p.a.

Avio S.p.a.

Elasis Sistema Ricerca Fiat Nel Mezzogiorno Societa Consortile Per Azioni

Paolo Altamura

Giulio Zagato

Marco Garabello

Gian Mario Bragallini

Michele Gravina

Alessio Gargioli

Giovanni Oddone

Edoardo Curti

Jan Biskupski

Marco Facchini

Gianluca Andrei

Leonardo Coviello

Davide Lauria

Leonardo Orlando

Antonio Caimano

Luca Ronchiato

Francesco Santacroce

Elio Perona

Massimo Civardi

Giorgio Rivetto

Salvatore Percacciolo

Cristiano Consales

Marco Maffiotto

A pitch lock system including an outer member having a centerline axis, an inner member located radially inward of the outer member with respect to the centerline axis, and a plurality of clutch elements located between the outer member and the inner member. The pitch lock system has a disengaged position and an engaged position. In the engaged position, the plurality of clutch elements are constrained between the inner member and the outer member such that relative axial direction of the plurality of clutch elements is permitted in only one direction. An engine includes a pitch actuator and the pitch lock system.

Hub assembly having a pitch lock system

A planetary gear system includes a carrier including a first side having a first oil manifold opening therethrough, and a second side having a second oil manifold opening therethrough, a first oil manifold and a second oil manifold. The first oil manifold has a first flange portion floatingly engaging with the first oil manifold opening, and a second flange portion engaging with the second oil manifold opening of the carrier, the second flange portion including a first oil manifold mounting flange. The second oil manifold has a second oil manifold flange portion engaging with the second oil manifold opening of the carrier, and including a second oil manifold mounting flange. At least one connecting member connects the first oil manifold mounting flange and the second oil manifold mounting flange so as to mount the first oil manifold and the second oil manifold to the carrier.

Floating oil manifold for planetary gear systems

A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades. The pitch change mechanism imparts a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades.

Variable pitch fan of a gas turbine engine

A turbomachine engine includes a fan assembly and a core engine comprising a turbine and an input shaft rotatable with the turbine is provided. A single-stage epicyclic gear assembly receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed. A sun gear rotates about a longitudinal centerline of the gear assembly and has a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact a plurality of planet gears. A ring gear-mesh region is provided along the longitudinal centerline of the gear assembly where a ring gear is configured to contact the plurality of planet gears. The sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline.

Turbomachines and epicyclic gear assemblies with axially offset sun and ring gears

A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.

Gas turbine engine

The present disclosure is directed to a turbine engine () defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly () comprising a gearbox; an engine core () comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft () defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.

Method and system of connecting a turbine engine gearbox to engine core

A gas turbine engine () includes a compressor section, a turbine section, and an accessory gearbox (). A turning unit () for the gas turbine engine includes an output assembly () configured to be mechanically coupled to the gas turbine engine, and an electric motor (). The electric motor is operable to rotate, through the output assembly, one or more components of the compressor section or the turbine section at a rotational speed less than about fifty revolutions per minute during a shut-down condition of the gas turbine engine.

Gas turbine engine turning system

The present disclosure is directed to a shaft assembly () for a turbine engine (), wherein the turbine engine includes a fan or propeller assembly () and an engine core (), and further wherein the fan or propeller assembly includes a gearbox (), and wherein the engine core includes one or more rotors (). The shaft assembly () includes a flexible shaft () defining a first end () and a second end () along the axial direction, wherein the first end is connected to the engine core () and the second end is connected to the gearbox (), and wherein a plurality of splines () is defined at the second end () and coupled to a spline interface () at the gearbox (); and a coupling () extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.

Flexible coupling shaft for turbine engine

A turbine engine defines an axial direction and a radial direction and includes a shaft assembly, a fan or propeller assembly, an engine core, a coupling shaft, a spacer, a sleeve, and a nut The coupling shaft defines an annular surface extended along the axial direction and a groove extended in a circumferential direction. The spacer defines a first portion disposed in the groove of the coupling shaft. The sleeve defines a threaded portion that extends along the axial direction and is disposed outward of the spacer in the radial direction. The nut defines a plurality of nut threads configured to mate with the plurality of sleeve threads of the sleeve. The nut defines a radial portion adjacent to at least a portion of the sleeve and at least a portion of the spacer in the axial direction.

Locknut sun gear for gas turbine engine

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

An output assembly for an accessory system of a gas turbine engine includes a first rotating member extending along an axis and including a mechanical connector for coupling the output assembly to an accessory system. The output assembly also including a second rotating member extending along the axis, the second rotating member coupled to the first rotating member at a first axial position and at a second axial position, the second rotating member coupled to the first rotating member at the second axial position through a one-way clutch. Additionally, the first rotating member of the output assembly further includes an extension member extending at least partially between the first axial position and the second axial position, the extension member including a designed fail point.

Output assembly for an accessory gearbox of a gas turbine engine

A rolling bearing is mounted on a gear shaft, which extends along an axis and carries a first and a second toothing axially separated from each other by a cylindrical portion of the gear shaft. Such a cylindrical portion has an outer diameter smaller than that of the first toothing. The bearing is provided with rolling bodies, a cage with seats engageable by the rolling bodies, and an outer ring defining an outer rolling path for the rolling bodies. During assembly, the cage is fitted around the first toothing and axially displaced towards the second toothing until it is arranged around the cylindrical portion. In this step, the tenons of the cage pass in the slots between the teeth of the first toothing. Subsequently, the rolling bodies are radially inserted in the respective seats so as to be arranged against the cylindrical portion.

Assembling process for mounting a rolling bearing on a gear shaft, and gear assembly obtainable by such a process

An accessory assembly of a turbine engine has a support structure and a shaft coupled to the support structure by means of a pair of main bearings and provided with an end portion, which has a shear neck designed to break when the torque transmitted to that shaft exceeds a predetermined design threshold; the accessory assembly also has a gear, which defines a motion inlet, is fixed to the end portion and, when said shear neck breaks, remains supported by a single secondary bearing; the latter is distinct from said main bearings and is arranged axially between said shear neck and the gear.

Accessory assembly of a turbine engine

An oil transfer assembly has a fixed structure, with at least one inlet for receiving lubricating oil, and an interface member rotating about an axis and having a front face, from which at least one duct starts for conveying the lubricating oil; the assembly is provided with a slide having an annular chamber, which is delimited axially, on one side, by the front face and connects the inlet with the duct; the slide is coupled to the front face so as to guarantee a seal for the fluid of the annular chamber and engages a guide seat provided in the structure in an axially sliding manner.

Growing community of inventors

Monopoli, Italy

Paolo Altamura