公开(公告)号：US20240125279A1

公开(公告)日：2024-04-18

申请号：US18393440

申请日：2023-12-21

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

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

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：US20240117769A1

公开(公告)日：2024-04-11

申请号：US18481597

申请日：2023-10-05

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

Inventor： Narayanan Payyoor ,  Weize Kang ,  Brandon W. Miller ,  Bugra H. Ertas ,  Andrea Piazza

IPC: F02C7/36 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/60 ,  F05D2260/40

Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.

公开(公告)号：US11945573B2

公开(公告)日：2024-04-02

申请号：US17529556

申请日：2021-11-18

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

Inventor： Mehdi Milani Baladi ,  Randy M Vondrell

IPC: B64C17/06 ,  B64C29/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02

CPC classification number: B64C17/06 ,  B64C29/0033 ,  B64D27/14 ,  B64D27/24 ,  B64D31/02 ,  B64D2027/026

Abstract: A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

公开(公告)号：US20240060559A1

公开(公告)日：2024-02-22

申请号：US18166605

申请日：2023-02-09

Applicant: GE Avio S.r.l.

Inventor： Giulio Zagato ,  Leonardo Coviello ,  Francesco Santacroce ,  Cristiano Consales ,  Paolo Altamura

IPC: F16H57/04 ,  F02C7/36

CPC classification number: F16H57/0486 ,  F16H57/042 ,  F02C7/36 ,  F05D2260/40311

Abstract: 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.

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：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：US11859546B2

公开(公告)日：2024-01-02

申请号：US17657685

申请日：2022-04-01

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

Inventor： Xiaohua Zhang ,  Bugra H. Ertas ,  Walter J. Smith ,  Flavia Turi

IPC: F16H57/04 ,  F02C7/06 ,  F02C7/36

CPC classification number: F02C7/06 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H57/0423 ,  F16H57/0456 ,  F16H57/0479

Abstract: A gearbox for a gas turbine engine. The gearbox including a rotor and a gutter. The oil system is configured to supply oil to the gearbox. The rotor is rotatable about a rotation axis. The rotor expels oil radially outward when the rotor rotates. The gutter is positioned radially outward of the rotor to collect oil expelled by the rotor when the rotor rotates. The gutter is positioned eccentrically with respect to the rotor.

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.