公开(公告)号：US12180896B2

公开(公告)日：2024-12-31

申请号：US18419892

申请日：2024-01-23

Applicant: GE Avio S.r.l.

Inventor： Pietro Molesini ,  Andrea Piazza ,  Fabio De Bellis

IPC: F02C7/36 ,  F01D25/18

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0.

公开(公告)号：US12110963B2

公开(公告)日：2024-10-08

申请号：US18450050

申请日：2023-08-15

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

Inventor： Leonardo Orlando ,  Juraj Hrubec

IPC: F16H57/08 ,  F16C19/38 ,  F16H1/28 ,  F16H3/66 ,  F16H3/44

CPC classification number: F16H57/08 ,  F16C19/38 ,  F16H1/28 ,  F16C2240/40 ,  F16C2240/70 ,  F16C2240/80 ,  F16C2240/82 ,  F16C2240/84 ,  F16C2361/65 ,  F16H3/44 ,  F16H3/66 ,  F16H3/663 ,  F16H3/666 ,  F16H2057/085

Abstract: A gearbox assembly includes a plurality of planet gears. At least one planet gear of the plurality of planet gears includes a layshaft. The gearbox assembly includes one or more roller bearings disposed within the layshaft and includes a plurality of rolling elements. The gearbox assembly also includes a bearing radial envelope in a range of 1.2 to 4.325. The gearbox assembly can also include a layshaft axial envelope in a range of 3.8 to 12.5.

公开(公告)号：US20240280164A1

公开(公告)日：2024-08-22

申请号：US18647737

申请日：2024-04-26

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

Inventor： Paolo Mastellone ,  Leonardo Coviello ,  Juraj Hrubec

IPC: F16H1/28 ,  F02C7/36 ,  F16H57/02 ,  F16H57/08

CPC classification number: F16H1/28 ,  F02C7/36 ,  F16H57/08 ,  F05D2260/40311 ,  F16H2057/02039 ,  F16H2057/085

Abstract: A gearbox assembly includes a plurality of planet gears. At least one planet gear of the plurality of planet gears includes a layshaft that supports a first stage planet gear and a second stage planet gear. The at least one planet gear is characterized by a Radial Stage Distance greater than or equal to 30 millimeters and less than or equal to 100 millimeters. The Radial Stage Distance is Rrm1−Rrt2. Rrm1 is a first stage rim inner radius of the first stage planet gear and Rrt2 is a second stage root radius of the second stage planet gear.

公开(公告)号：US12065936B2

公开(公告)日：2024-08-20

申请号：US17409943

申请日：2021-08-24

Applicant: GE Avio S.r.l.

Inventor： Cristian Lizzer ,  Maciej Slawinski ,  Wojciech Lukasz Staszynski ,  Jan Biskupski

IPC: F01D17/02 ,  F01D9/04

CPC classification number: F01D17/02 ,  F01D9/041 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/80

Abstract: An inter-turbine duct is positioned between a high pressure turbine and a low pressure turbine of a gas turbine engine. The inter-turbine duct includes an inner annular wall and an outer annular wall spaced apart from the inner annular wall along a radial direction to define an annular flow passage. The inter-turbine duct includes a plurality of circumferentially spaced vanes positioned within the flow passage and at least one temperature probe is positioned upstream of the vanes at a circumferential location that is between thirty and seventy percent of a circumferential distance between the leading edges of adjacent vanes.

公开(公告)号：US20240151240A1

公开(公告)日：2024-05-09

申请号：US18316656

申请日：2023-05-12

Applicant: GE Avio S.r.l.

Inventor： Paolo Altamura ,  Giulio Zagato

IPC: F04D29/32 ,  B64C11/32

CPC classification number: F04D29/323 ,  B64C11/32 ,  F05D2220/32 ,  F05D2260/74 ,  F05D2260/79

Abstract: 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.

公开(公告)号：US20240149526A1

公开(公告)日：2024-05-09

申请号：US18313901

申请日：2023-05-08

Applicant: GE Avio S.R.L.

Inventor： Agostino Scialpi ,  Edoardo Maria Peradotto ,  Giuseppe Greco

IPC: B29C64/218 ,  B29C64/153 ,  B29C64/295

CPC classification number: B29C64/218 ,  B29C64/153 ,  B29C64/295 ,  B33Y30/00

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to generate a tailored grain size in an additive manufacturing environment. Disclosed herein is an apparatus comprising controller circuitry to determine a configuration for manufacture of a part, the part having a first portion and a second portion, an additive manufacturing machine to manufacture the part according to the configuration, and a force application device to apply a force to the part during manufacture, the force specified in the configuration to produce a desired grain size, the desired grain size including a first grain size and a second grain size, wherein the first portion is formed with the first grain size and the second portion is formed with the second grain size.

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.