公开(公告)号：US20250035052A1

公开(公告)日：2025-01-30

申请号：US18913330

申请日：2024-10-11

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

Inventor： Bugra H. Ertas ,  Ravindra Shankar Ganiger ,  Andrea Piazza ,  Brandon W. Miller

IPC: F02C7/36

Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.

公开(公告)号：US20250026470A1

公开(公告)日：2025-01-23

申请号：US18439870

申请日：2024-02-13

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

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：US12203418B2

公开(公告)日：2025-01-21

申请号：US17929105

申请日：2022-09-01

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

Inventor： Bugra H. Ertas ,  Ravindra Shankar Ganiger ,  Andrea Piazza

IPC: F02C7/36 ,  F16H57/025 ,  F16H57/08

Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling.

公开(公告)号：US20250003482A1

公开(公告)日：2025-01-02

申请号：US18510014

申请日：2023-11-15

Applicant: GE Avio S.r.l.

Inventor： Miriam Manzoni ,  Michele Gravina ,  Federico Leonardi ,  Alessandro Anderlini

IPC: F16H57/04

Abstract: A lubrication system for a gear assembly. The gear assembly includes a first gear and a second gear. The first gear and the second gear mesh with each other at a mesh. The lubrication system includes one or more lubricant injectors. The one or more lubricant injectors include one or more first lubricant outlets directed to the mesh. The one or more first lubricant outlets supply a first portion of lubricant to the mesh. The one or more lubricant injectors include one or more second lubricant outlets directed to a location that is different than the mesh. The one or more second lubricant outlets supply a second portion of lubricant to the location different than the mesh.

公开(公告)号：US12168239B2

公开(公告)日：2024-12-17

申请号：US17643544

申请日：2021-12-09

Applicant: GE Avio S.r.l.

Inventor： Saypen Baraggia Au Yeung ,  Pietro Molesini ,  Miriam Manzoni ,  Fabio De Bellis

IPC: B01D45/16 ,  B04C5/04 ,  B04C5/28 ,  F02C7/06

Abstract: An air/oil separator is provided. The air/oil separator includes an oil manifold having a first air/oil inlet and a second air/oil inlet; a first separation chamber in communication with the first air/oil inlet; and a second separation chamber separate from the first separation chamber, the second separation chamber in communication with the second air/oil inlet.

公开(公告)号：US12110903B2

公开(公告)日：2024-10-08

申请号：US18316656

申请日：2023-05-12

Applicant: GE Avio S.r.l.

Inventor： Paolo Altamura ,  Giulio Zagato

IPC: F04D29/32 ,  B64C11/06 ,  B64C11/32 ,  B64C11/36 ,  B64C11/38 ,  B64C11/42 ,  F02K3/06

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：US20240280170A1

公开(公告)日：2024-08-22

申请号：US18477960

申请日：2023-09-29

Applicant: GE Avio S.r.l.

Inventor： Michele Gravina ,  Miriam Manzoni ,  Federico Leonardi ,  Andrea Piazza

IPC: F16H57/04

CPC classification number: F16H57/0471 ,  F16H57/0424 ,  F16H57/0428 ,  F16H57/0443 ,  F02C7/36

Abstract: A gearbox assembly includes a plurality of planet gears secured by a planet carrier. The plurality of planet gears and the planet carrier rotate about a longitudinal centerline axis. A planet pin is disposed in each planet gear. One or more journal bearings are defined by the planet pin and the planet gear, each planet gear rotating about the one or more journal bearings. The gearbox assembly includes an auxiliary lubrication system that stores lubricant therein. The auxiliary lubrication system includes one or more lubricant lines that provide fluid communication between the auxiliary lubrication system and the one or more journal bearings. Rotation of the planet carrier and the one or more journal bearings generates a suction effect that causes the lubricant in the auxiliary lubrication system to flow to the one or more journal bearings during windmilling conditions and during zero gravity conditions or negative gravity conditions.

公开(公告)号：US20240254884A1

公开(公告)日：2024-08-01

申请号：US18635858

申请日：2024-04-15

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：US20240254882A1

公开(公告)日：2024-08-01

申请号：US18594594

申请日：2024-03-04

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

Inventor： Saurya Ranjan Ray ,  Francesco Bertini ,  Lyle Douglas Dailey ,  Jeffrey D. Clements ,  Jaikumar Loganathan ,  Simone Rosa Taddei

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2240/301 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/181 ,  F05D2250/711 ,  F05D2250/712

Abstract: An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.

公开(公告)号：US12049849B2

公开(公告)日：2024-07-30

申请号：US18209689

申请日：2023-06-14

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

Inventor： Andrea Piazza ,  Jeffrey D. Clements

IPC: F02C7/36 ,  F02C3/067 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02C3/067 ,  F02K3/06 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2200/221 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0. The overall engine efficiency rating is greater than or equal to 0.35GR1.5 and less than or equal to 0.7GR1.5.