公开(公告)号：US20190390604A1

公开(公告)日：2019-12-26

申请号：US16482024

申请日：2018-01-24

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini

IPC: F02C7/32 ,  F16D1/06 ,  F16C19/26 ,  F16C33/58 ,  F16C35/063

Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine (10) defines an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly (14) includes a gearbox (45). The turbine engine (10) includes a coupling shaft (100), a spacer (150), a sleeve (200), and a nut (250) in adjacent radial arrangement. The coupling shaft (100) is connected at a first end (97) to the engine core (20) and coupled at a second end (96) to the gearbox (45). The coupling shaft (100) defines an annular surface (103) extended along the axial direction and a groove (104) extended in a circumferential direction. The spacer (150) defines a first portion (151) extended inward in the radial direction and a second portion (152) extended in the axial direction. The first portion (151) is disposed in the groove (104) of the coupling shaft (100). The sleeve (200) defines a threaded portion (202) comprising a plurality of sleeve threads (204) defined outwardly in the radial direction. The threaded portion (202) extends along the axial direction and is disposed outward of the (spacer 150) in the radial direction. The nut (250) defines a plurality of nut threads (252) defined inwardly in the radial direction. The plurality of nut threads (252) of the nut (250) is configured to mate with the plurality of sleeve threads (204) of the sleeve (200). The (nut 250) defines a radial portion (254) extended inward in the radial direction. The radial portion (254) is adjacent to at least a portion of the sleeve (200) and at least a portion of the spacer (150) in the axial direction.

公开(公告)号：US20140309078A1

公开(公告)日：2014-10-16

申请号：US14356129

申请日：2012-11-02

Applicant: GE AVIO S.R.L.

Inventor： Edoardo Curti ,  Michele Gravina ,  Giulio Zagato ,  Luca Ronchiato ,  Elio Perona ,  Paolo Altamura

IPC: F16H1/28

CPC classification number: F16H1/28 ,  F02C7/36 ,  F05D2260/40311 ,  F16H1/2827 ,  F16H2001/289 ,  Y02T50/671

Abstract: An epicyclic gearing has a plurality of planet gears arranged about a transmission axis so as to form two arrays symmetrical with respect to a plane orthogonal to the transmission axis; the gearing has a body which, on one side, is adapted to be connected to a rotating member and, on the other side, is coupled to a ring; the ring has a plurality of relatively thin plate sectors and a plurality of pins, which extend in cantilever fashion and in opposite directions from the plate sectors and each support a respective planet gear; coupling between the aforesaid body and the ring defines at least one degree of freedom in rotation about a radial axis to allow a relative movement under load between the two components.

Abstract translation: 行星齿轮传动装置具有围绕传动轴布置的多个行星齿轮，以形成相对于与传动轴正交的平面对称的两个阵列; 传动装置具有一体，其一侧适于连接到旋转部件，另一侧与环相连; 环具有多个相对较薄的板扇区和多个销，其以悬臂方式延伸并且在与板扇区相反的方向上延伸，并且每个支撑相应的行星齿轮; 上述主体和环之间的联接限定了围绕径向轴线的至少一个旋转自由度，以允许两个部件之间的负载下的相对运动。

公开(公告)号：US20240359793A1

公开(公告)日：2024-10-31

申请号：US18525315

申请日：2023-11-30

Applicant: GE AVIO S.R.L

Inventor： Diego Di Leo ,  Giuseppe Cervelli ,  Paolo Altamura

IPC: B64C11/38

CPC classification number: B64C11/38

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to control propeller pitch in dual acting propellers. An example propeller control system comprising: a piston including a piston rod; a first valve connected to the piston rod via a first piston line and a second piston line, wherein the first valve selectively allows, based on an input signal, hydraulic fluid to transfer to the piston via the first piston line and the second piston line, wherein in the first valve is a three-state valve; and an independent valve connected to the piston rod via a third piston line, wherein the independent valve selectively allows, based on an input signal, hydraulic fluid to transfer to the piston via the third piston line and wherein the independent valve operates independently of the first valve.

公开(公告)号：US12078075B2

公开(公告)日：2024-09-03

申请号：US18091753

申请日：2022-12-30

Applicant: GE Avio S.r.l.

Inventor： Marco Facchini ,  Gianluca Andrei ,  Paolo Altamura

IPC: F02C7/36 ,  F01D5/02 ,  F01D25/00 ,  F16H1/28 ,  F16H1/32 ,  F16H1/46 ,  F16H3/44 ,  F16H57/08

CPC classification number: F01D25/00 ,  F01D5/022 ,  F02C7/36 ,  F16H1/2809 ,  F16H1/32 ,  F16H1/46 ,  F16H3/44 ,  F16H57/08 ,  F05D2260/40311 ,  F16H2001/289

Abstract: 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.

公开(公告)号：US20240240566A1

公开(公告)日：2024-07-18

申请号：US18456817

申请日：2023-08-28

Applicant: GE Avio S.r.l.

Inventor： Paolo Altamura ,  Giulio Zagato

IPC: F01D7/00 ,  F15B15/02

CPC classification number: F01D7/00 ,  F15B15/02 ,  F05D2260/30

Abstract: 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.

公开(公告)号：US11542829B2

公开(公告)日：2023-01-03

申请号：US17307948

申请日：2021-05-04

Applicant: GE Avio S.r.l.

Inventor： Marco Facchini ,  Gianluca Andrei ,  Paolo Altamura

IPC: F16H1/28 ,  F01D25/00 ,  F01D5/02 ,  F16H1/46 ,  F02C7/36 ,  F16H3/44 ,  F16H57/08 ,  F16H1/32

Abstract: 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.

公开(公告)号：US11161598B2

公开(公告)日：2021-11-02

申请号：US16481708

申请日：2018-01-26

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini ,  Davide Lauria

IPC: B64C11/40 ,  B64C11/38 ,  B64C11/42 ,  F01D7/00

Abstract: 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.

公开(公告)号：US20190383331A1

公开(公告)日：2019-12-19

申请号：US16482065

申请日：2018-01-26

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini ,  Alessio Gargioli ,  Jan Biskupski

IPC: F16D3/74 ,  F02C7/36 ,  F16D7/00 ,  F16D3/12

Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.

公开(公告)号：US09797475B2

公开(公告)日：2017-10-24

申请号：US14721992

申请日：2015-05-26

Applicant: GE AVIO S.R.L.

Inventor： Paolo Altamura

IPC: F16H57/04 ,  F16H1/28 ,  F16H57/08

CPC classification number: F16H1/2836 ,  F16H57/043 ,  F16H57/0479 ,  F16H57/082 ,  F16H2057/085

Abstract: An epicyclic transmission has a sun gear rotating about a transmission axis, a planet carrier provided with a plurality of tenons, which extend along respective supporting axes, and a plurality of planet gears meshing with the sun gear and supported by the tenons, by means of the interposition of bearings which allow the planet gears to rotate about respective rotation axes, parallel to the transmission axis; the inner rings of the bearings are coupled to the tenons in a swiveling manner by means of joint devices defined by cylindrical hinges which hinge about hinge axes which are fixed with respect to the tenons and lay on a plane orthogonal to the transmission and rotation axes.

公开(公告)号：US20170114884A1

公开(公告)日：2017-04-27

申请号：US15126877

申请日：2015-03-18

Applicant: GE AVIO S.r.l.

Inventor： Paolo Altamura

IPC: F16H57/04 ,  F16L27/08

Abstract: 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.