-
公开(公告)号：US11555521B2
公开(公告)日：2023-01-17
申请号：US17074906
申请日：2020-10-20
Applicant: GE Avio S.r.l.
Inventor： Tomasz Kowalewski , Ivan Borra , Gian Mario Bragallini , Vincenzo Giordano
Abstract: A gearbox comprising a main unit comprising a first casing and a first hollow shaft, and a secondary unit comprising a second casing and a second hollow shaft, and a drive shaft comprising a first clutch portion and a second clutch portion, which engage the first and second hollow shafts in an angularly fixed and axially sliding manner. The gearbox further including an axial retaining device comprising an axial shoulder supported in a fixed potion by an axial end on one of the first or second hollow shafts, and an external radial projection arranged in an intermediate position, and an external radial projection arranged in an intermediate position along the drive shaft between the first and second clutch portions.
-
公开(公告)号：US20220397040A1
公开(公告)日：2022-12-15
申请号：US17835879
申请日：2022-06-08
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Fabio De Bellis , Andrea Piazza
Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.
-
公开(公告)号：US11519346B2
公开(公告)日：2022-12-06
申请号：US16920159
申请日：2020-07-02
Applicant: GE Aviation Czech s.r.o. , GE Avio S.r.l.
Inventor： Giuseppe Cervelli , Simone Castellani , Miriam Manzoni , Giuseppe Bellocchio , Vojtech Jirasek
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：US11473507B2
公开(公告)日：2022-10-18
申请号：US17364707
申请日：2021-06-30
Applicant: GE Avio S.r.l.
Inventor： Pietro Molesini , Andrea Piazza , Fabio De Bellis
Abstract: A turbomachine engine can include a fan assembly, a pitch change mechanism, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The pitch change mechanism can be coupled to the fan assembly. The vane assembly can include a plurality of vanes. 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, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.
-
公开(公告)号：US20220184641A1
公开(公告)日：2022-06-16
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
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.
-
Patent Agency Ranking
公开(公告)号：US20220097864A1
公开(公告)日：2022-03-31
申请号：US17471774
申请日：2021-09-10
Applicant: GE Avio S.r.l.
Inventor： Mehdi M. Baladi , Aniello Esposito , Sridhar Adibhatla , Kathleen K. Collins
Abstract: A system and method for optimizing performance of an aircraft or boat through detection and trending of engine deterioration based on the performance of the vehicle's gas turbine. The system and method detects declines in engine power due to either of in-transit events or over the extended lifetime of the engine, the declines being due to routine engine part aging or an event. As engine power gradually or suddenly deteriorates, the system and method lowers a maximum operating line which defines the safe limits for peak engine power consumption during flight. For in-transit events, the system and method detects when actual power consumption is approaching the current maximum operating line. The controller may then automate changes to operations of entirely separate aircraft systems, such as rebalancing electrical energy consumption by various non-engine elements of the aircraft.
-
公开(公告)号：US11286976B2
公开(公告)日：2022-03-29
申请号：US17014189
申请日：2020-09-08
Applicant: GE Avio S.r.l.
Inventor： Andrea Donnini , Ivan Borra
Abstract: An axially hyperstatic system softener for a transmission comprising a static component and a rotatable component mounted to each other by a double ball bearing having an outer race and an inner race includes first and second biasing elements in a rigid sleeve with the outer race disposed between the first and second biasing elements. The rotatable component includes two shafts splined together with the static component mounted to one of the shafts by the bearing double ball bearing. A shim between one of the biasing elements and the sleeve enables tuning the softener.
-
公开(公告)号：US20210404348A1
公开(公告)日：2021-12-30
申请号：US17307262
申请日：2021-05-04
Applicant: GE Avio S.r.l.
Inventor： Alberto Buonvino , Luca Giacobone , Daniele Coutandin
Abstract: Aspects of the disclosure generally relate to a turbine engine and method of operating, wherein a change in sealing status can be determined within a cavity between an outer casing and a rotor within the turbine engine. Aspects of the disclosure further relate to a supply of air to the cavity within the turbine engine.
-
公开(公告)号：US20210348521A1
公开(公告)日：2021-11-11
申请号：US17307948
申请日：2021-05-04
Applicant: GE Avio S.r.l.
Inventor： Marco Facchini , Gianluca Andrei , Paolo Altamura
Abstract: A turbomachine engine includes a fan assembly and a core engine comprising a turbine and an input shaft rotatable with the turbine is provided. A single-stage epicyclic gear assembly receives the input shaft at a first speed and drives an output shaft coupled to the fan assembly at a second speed. A sun gear rotates about a longitudinal centerline of the gear assembly and has a sun gear-mesh region along the longitudinal centerline of the gear assembly where the sun gear is configured to contact a plurality of planet gears. A ring gear-mesh region is provided along the longitudinal centerline of the gear assembly where a ring gear is configured to contact the plurality of planet gears. The sun gear-mesh region is axially offset from the ring gear-mesh region along the longitudinal centerline.
-
公开(公告)号：US20210270189A1
公开(公告)日：2021-09-02
申请号：US17150136
申请日：2021-01-15
Applicant: GE Avio S.r.l.
Inventor： Juraj Hrubec , Davide Lauria
Abstract: A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.
-
-
-
-
-
-
-
-
-
Search Results
299
records
(took 0.015 seconds)
