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公开(公告)号：US10578206B2
公开(公告)日：2020-03-03
申请号：US15126877
申请日：2015-03-18
Applicant: GE AVIO S.r.l.
Inventor： Paolo Altamura
Abstract: An oil transfer assembly has a fixed structure, with at least one inlet for receiving lubricating oil, and an interface member rotating about an axis and having a front face, from which at least one duct starts for conveying the lubricating oil; the assembly is provided with a slide having an annular chamber, which is delimited axially, on one side, by the front face and connects the inlet with the duct; the slide is coupled to the front face so as to guarantee a seal for the fluid of the annular chamber and engages a guide seat provided in the structure in an axially sliding manner.
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公开(公告)号：US20190389562A1
公开(公告)日：2019-12-26
申请号：US16481708
申请日：2018-01-26
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Paolo Altamura , Gian Mario Bragallini , Davide Lauria
Abstract: The present disclosure is directed to a system 100 for feathering a propeller assembly 14, wherein the system is disposed within a housing 47 of the propeller assembly. The system 100 includes a sleeve 110 defining an outer wall 111 and one or more sleeve tabs 115 extended outward in a radial direction along at least a circumferential portion of the sleeve, wherein the one or more sleeve tabs is separated from the outer wall in an axial direction. The system 100 further includes a retainer 120 defining one or more retainer tabs 125 extended inward in the radial direction, wherein the one or more retainer tabs is disposed between the outer wall 111 and the one or more sleeve tabs 115 of the sleeve 110 along the axial direction. Still further, the system includes a beta tube assembly 130 extended through the sleeve along the axial direction, wherein the beta tube assembly defines one or more internal walls 131, wherein the one or more internal walls defines a hydraulic fluid transfer cavity 132 in fluid communication with one or more hydraulic fluid transfer orifices 133.
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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
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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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.
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公开(公告)号：US10415693B2
公开(公告)日：2019-09-17
申请号：US15384179
申请日：2016-12-19
Applicant: GE Avio S.r.l.
Inventor： Paolo Altamura
Abstract: An oil transfer assembly supplies oil into a moving, rotating tube extending along an axis. The assembly is provided with a support plate transversal to the axis and a sleeve, which is angularly fixed with respect to the support plate, it is configured to be coupled in a sliding and watertight way to a terminal section of the inlet of said tube and has at least one chamber for transferring oil into said terminal section of the inlet. The assembly is also equipped with at least two tubular bodies, which project axially from the support plate, define between them an annular channel communicating with the chamber and join the sleeve to the support plate in a watertight manner and with clearances so as to leave freedom of orientation of the sleeve around any direction orthogonal to the axis.
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Patent Agency Ranking
公开(公告)号：US09103413B2
公开(公告)日：2015-08-11
申请号：US14356129
申请日：2012-11-02
Applicant: GE AVIO S.R.L.
Inventor： Edoardo Curti , Michele Gravina , Giulio Zagato , Luca Ronchiato , Elio Perona , Paolo Altamura
CPC classification number: F16H1/28 , F02C7/36 , F05D2260/40311 , F16H1/2827 , F16H2001/289 , Y02T50/671
Abstract: An epicyclic gearing has a plurality of planet gears arranged about a transmission axis so as to form two arrays symmetrical with respect to a plane orthogonal to the transmission axis; the gearing has a body which, on one side, is adapted to be connected to a rotating member and, on the other side, is coupled to a ring; the ring has a plurality of relatively thin plate sectors and a plurality of pins, which extend in cantilever fashion and in opposite directions from the plate sectors and each support a respective planet gear; coupling between the aforesaid body and the ring defines at least one degree of freedom in rotation about a radial axis to allow a relative movement under load between the two components.
Abstract translation: 行星齿轮传动装置具有围绕传动轴布置的多个行星齿轮，以形成相对于与传动轴正交的平面对称的两个阵列; 传动装置具有一体，其一侧适于连接到旋转部件，另一侧与环相连; 环具有多个相对较薄的板扇区和多个销，其以悬臂方式延伸并且在与板扇区相反的方向上延伸，并且每个支撑相应的行星齿轮; 上述主体和环之间的联接限定了围绕径向轴线的至少一个旋转自由度，以允许两个部件之间的负载下的相对运动。
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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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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
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.
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公开(公告)号：US11591969B2
公开(公告)日：2023-02-28
申请号：US16482086
申请日：2018-01-24
Applicant: GE Avio S.r.l.
Inventor： Marco Garabello , Paolo Altamura , Gian Mario Bragallini , Alessio Gargioli , Jan Biskupski
Abstract: The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.
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公开(公告)号：US11536202B2
公开(公告)日：2022-12-27
申请号：US16497951
申请日：2018-03-23
Applicant: GE Avio S.r.l.
Inventor： Antonio Caimano , Paolo Altamura , Massimo Civardi , Giorgio Rivetto
Abstract: A gas turbine engine (10) includes a compressor section, a turbine section, and an accessory gearbox (100). A turning unit (200) for the gas turbine engine includes an output assembly (204) configured to be mechanically coupled to the gas turbine engine, and an electric motor (202). The electric motor is operable to rotate, through the output assembly, one or more components of the compressor section or the turbine section at a rotational speed less than about fifty revolutions per minute during a shut-down condition of the gas turbine engine.
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