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公开(公告)号：US20250137529A1
公开(公告)日：2025-05-01
申请号：US19003582
申请日：2024-12-27
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Xiaohua Zhang , Miriam Manzoni , Flavia Turi , Andrea Piazza , Arthur W. Sibbach
Abstract: A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3. The lubricant extraction volume ratio defined by: V G V GB . V G is a gutter volume of the gutter and VGB is a gearbox volume. The gas turbine engine includes a lubrication system that includes a lubricant tank that stores lubricant, one or more primary gearbox lubricant supply lines, one or more secondary gearbox lubricant supply lines, and a lubricant pump for supplying the lubricant to the gearbox assembly through the primary gearbox lubricant supply lines and the secondary gearbox lubricant supply lines. The lubrication system modulates a mass flow rate of the lubricant to the gearbox assembly through the primary gearbox lubricant supply lines or the secondary gearbox lubricant supply lines.
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公开(公告)号：US12276558B2
公开(公告)日：2025-04-15
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
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.
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公开(公告)号：US20250116208A1
公开(公告)日：2025-04-10
申请号：US18751984
申请日：2024-06-24
Applicant: GE Avio S.r.l.
Inventor： Andrea Piazza
Abstract: A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a fuel system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump. The fuel system stores hydrogen fuel. The fuel system includes a fuel cell controller that generates electricity from the hydrogen fuel. The electricity powers the auxiliary pump when the propulsor is windmilling such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.
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公开(公告)号：US20250116207A1
公开(公告)日：2025-04-10
申请号：US18751978
申请日：2024-06-24
Applicant: GE Avio S.r.l.
Inventor： Andrea Piazza
IPC: F01D25/20
Abstract: A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a strain energy storage system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump including an auxiliary pump shaft. The strain energy storage system includes a spring drivingly coupled to the auxiliary pump shaft. The spring stores strain energy during normal operation of the turbine engine and releases the strain energy when the propulsor is windmilling to rotate the auxiliary pump shaft to power the auxiliary pump such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.
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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
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.
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Patent Agency Ranking
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
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.
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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
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.
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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
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.
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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
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.
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10.发明公开公开(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.
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