公开(公告)号：US11905853B2

公开(公告)日：2024-02-20

申请号：US17228778

申请日：2021-04-13

Applicant: GE Avio S.r.l.

Inventor： Alberto Buonvino ,  Luca Giacobone ,  Daniele Coutandin ,  Ernesto Sozio ,  Francesco Bertini

IPC: F01D9/04 ,  F01D5/14 ,  F01D11/00

CPC classification number: F01D9/041 ,  F01D5/14 ,  F01D5/141 ,  F01D11/001 ,  F01D11/006 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30

Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.

公开(公告)号：US11885233B2

公开(公告)日：2024-01-30

申请号：US17876009

申请日：2022-07-28

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Ernesto Sozio ,  Francesco Bertini ,  Jeffrey Donald Clements ,  Jonathan Ong ,  Lyle Douglas Dailey ,  Paul Hadley Vitt ,  Matteo Renato Usseglio

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/54

CPC classification number: F01D5/141 ,  F04D29/324 ,  F04D29/544 ,  F05D2220/32 ,  F05D2240/30

Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).

公开(公告)号：US11873771B2

公开(公告)日：2024-01-16

申请号：US18061852

申请日：2022-12-05

Applicant: GE Aviation Czech s.r.o. ,  GE Avio S.r.l.

Inventor： Giuseppe Cervelli ,  Simone Castellani ,  Miriam Manzoni ,  Giuseppe Bellocchio ,  Vojtech Jirasek

IPC: F02D29/02 ,  B64C11/38 ,  B64C11/40 ,  B63H3/10 ,  F02B61/04

CPC classification number: F02D29/02 ,  B64C11/385 ,  B64C11/40 ,  B63H3/10 ,  F02B61/045

Abstract: A variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.

公开(公告)号：US11873767B2

公开(公告)日：2024-01-16

申请号：US17508545

申请日：2021-10-22

Applicant: GE Avio S.r.l. ,  General Electric Company

Inventor： Andrea Piazza ,  Darek Zatorski ,  Juraj Hrubec ,  David M. Ostdiek

IPC: F02C7/36 ,  F01D1/24

CPC classification number: F02C7/36 ,  F01D1/24 ,  F05D2220/36 ,  F05D2260/40311

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and is driven by the input shaft. A component of the gear assembly drives the output shaft. The gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

公开(公告)号：US20240009923A1

公开(公告)日：2024-01-11

申请号：US18218677

申请日：2023-07-06

Applicant: GE Avio S.r.l.

Inventor： Edoardo Maria Peradotto ,  Emanuele Quarona ,  Alessandro De Grassi

IPC: B29C64/218 ,  B29C64/118 ,  B33Y10/00 ,  B33Y30/00

CPC classification number: B29C64/218 ,  B29C64/118 ,  B33Y10/00 ,  B33Y30/00

Abstract: An additive manufacturing system for producing a component includes a deposition assembly having a deposition head through which melted feedstock material is deposited, and a compression rig comprising a compression head supporting an inside roller, an outside roller opposing the inside roller, and a top roller, the inside roller applying a compressive load onto an interior side surface of the component, the outside roller applying a compressive load onto an exterior side surface of the component, and the top roller applying a compressive load onto a top surface of the component.

公开(公告)号：US20230399983A1

公开(公告)日：2023-12-14

申请号：US17806574

申请日：2022-06-13

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Ravindra Shankar Ganiger ,  Andrea Piazza ,  Gontla Nagashiresha ,  Bugra H. Ertas ,  Sanjeev Jha

IPC: F02C7/36 ,  F01D15/10 ,  F02K3/06

CPC classification number: F02C7/36 ,  F01D15/10 ,  F02K3/06 ,  F05D2220/768 ,  F05D2260/40311

Abstract: A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

公开(公告)号：US20230374935A1

公开(公告)日：2023-11-23

申请号：US17747497

申请日：2022-05-18

Applicant: General Electric Company ,  GE Avio S.r.l. ,  General Electric Deutschland Holding GmbH

Inventor： Paul Hadley Vitt ,  Lyle Douglas Dailey ,  Matteo Renato Usseglio ,  Andreas Peters

IPC: F02C3/067 ,  F02C6/00 ,  F02C7/36

CPC classification number: F02C3/067 ,  F02C6/00 ,  F02C7/36 ,  F05D2220/76

Abstract: A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial direction

公开(公告)号：US20230314254A1

公开(公告)日：2023-10-05

申请号：US17888856

申请日：2022-08-16

Applicant: GE Avio S.r.l.

Inventor： Simone Recchia ,  Diego di Leo ,  Pierpaolo Forte ,  Cristian Lai

IPC: G01L25/00 ,  G01L5/00 ,  F02C9/00

CPC classification number: G01L25/003 ,  G01L5/00 ,  F02C9/00

Abstract: Input is received. A conformance is determined. When conformance is determined, a raw torque is measured from a torque sensor at an engine; the raw torque is calibrated using the torque sensor parameters to produce a calibrated torque value, non-torque parameters associated with the engine are measured and the non-torque parameters are applied to a lookup structure to obtain an expected torque value. A separation of the calibrated torque value and the expected torque value is determined and based upon the separation, an operation of the torque sensor is controlled.

公开(公告)号：US20230296024A1

公开(公告)日：2023-09-21

申请号：US17951653

申请日：2022-09-23

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Francesco Bertini ,  Davide Torzo ,  Pratish Patil ,  John Joseph ,  Mahendran Manoharan ,  Ganesh Seshadri

IPC: F01D5/14

CPC classification number: F01D5/142 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/30

Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.

公开(公告)号：US11739643B2

公开(公告)日：2023-08-29

申请号：US17154153

申请日：2021-01-21

Applicant: GE Avio S.r.l.

Inventor： Alberto Buonvino ,  Daniele Coutandin ,  Luca Giacobone ,  Riccardo Da Soghe ,  Cosimo Bianchini

IPC: F01D5/08 ,  F02C3/067 ,  F02C6/08 ,  F01D5/03

CPC classification number: F01D5/085 ,  F02C3/067 ,  F02C6/08 ,  F01D5/03 ,  F05D2260/232 ,  F05D2260/606

Abstract: A turbine engine having counter-rotating rotors comprising a first rotor, rotating in a first rotational direction, defining a first rotor set of blades axially spaced to define a gap, and a second rotor, rotating in a second rotational direction counter the first rotational direction. The second rotor further including a second set of blades received within the gap of the first rotor. A plurality of fluid passages is formed in the first rotor with an outlet facing the gap.