公开(公告)号：US10753456B2

公开(公告)日：2020-08-25

申请号：US15492045

申请日：2017-04-20

Applicant: GE Avio S.r.I.

Inventor： Lorenzo Cipolla ,  Michele Gravina

IPC: F16H57/04 ,  F02C7/36 ,  F02C7/06 ,  F01D25/16 ,  F01D25/18

Abstract: An oil transfer unit has a rotating part extending along an axis, a stationary part provided with an oil mouth, and a floating part coupled to the stationary part; the floating part is provided with a cylindrical surface fitted onto an outer cylindrical surface of the rotating part in a non-contact configuration, with an annular groove therebetween to put the oil mouth into communication with an inner chamber of the rotating part; both sides of the groove are sealed by oil films at a radial gap between the cylindrical surfaces of the floating and rotating parts; the unit has a plurality of recesses, which are delimited outwardly by the floating part and inwardly by the rotating part, are arranged on the opposite axial sides of the groove so as to locally enlarge the radial distance with respect to the radial gap and are inwardly closed by the rotating part.

公开(公告)号：US10578166B2

公开(公告)日：2020-03-03

申请号：US15521067

申请日：2015-10-22

Applicant: GE AVIO S.r.l.

Inventor： Paolo Altamura

IPC: F16D9/08 ,  F02C7/06 ,  F02C7/32 ,  F01D25/16 ,  F01D21/00

Abstract: An accessory assembly of a turbine engine has a support structure and a shaft coupled to the support structure by means of a pair of main bearings and provided with an end portion, which has a shear neck designed to break when the torque transmitted to that shaft exceeds a predetermined design threshold; the accessory assembly also has a gear, which defines a motion inlet, is fixed to the end portion and, when said shear neck breaks, remains supported by a single secondary bearing; the latter is distinct from said main bearings and is arranged axially between said shear neck and the gear.

公开(公告)号：US09523424B2

公开(公告)日：2016-12-20

申请号：US14698723

申请日：2015-04-28

Applicant: GE AVIO S.R.L.

Inventor： Paolo Altamura

IPC: F16H57/04 ,  F16H57/08

CPC classification number: F16H57/0479 ,  F16H57/0427 ,  F16H57/043 ,  F16H57/0434 ,  F16H57/0441 ,  F16H57/0456 ,  F16H57/046 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/082

Abstract: An epyciclic transmission has a sun gear rotational about a transmission axis, a plurality of planet wheels meshing with the sun gear, and a carrier which supports the planet wheels and is rotational about the transmission axis; the transmission also has a lubricating system provided with at least one nozzle arranged in fixed position, with a collection channel fixed with respect to the carrier and configured to receive a jet of oil exiting from the nozzle, and with at least one pump having a casing fixed to the carrier; the pump is actuated by means of a transmission device in response to the rotation of the carrier to pump the oil from the collection channel to zones on the carrier which require lubrication.

Abstract translation: 一个太阳齿轮围绕传动轴转动太阳齿轮，与太阳齿轮啮合的多个行星轮，以及支撑行星轮并围绕传动轴旋转的载体; 所述变速器还具有设置有至少一个布置在固定位置的喷嘴的润滑系统，其中收集通道相对于所述载体固定并且构造成接收从所述喷嘴出来的油喷射器，并且至少一个泵具有壳体 固定在承运人身上 响应于载体的旋转，泵通过传动装置致动，以将油从收集通道泵送到需要润滑的载体上的区域。

公开(公告)号：US09427816B2

公开(公告)日：2016-08-30

申请号：US14276597

申请日：2014-05-13

Applicant: GE AVIO S.r.l.

Inventor： Salvatore Milletari ,  Rinaldo Siccardi

IPC: B23Q15/20 ,  B23F23/12 ,  B23B31/02 ,  B23F23/06 ,  B23B41/00 ,  B23B25/06 ,  B23F17/00 ,  B23F19/00 ,  B23F23/04

CPC classification number: B23F23/1218 ,  B23B25/06 ,  B23B31/025 ,  B23B41/00 ,  B23F17/006 ,  B23F19/00 ,  B23F23/04 ,  B23F23/06 ,  B23Q2716/00 ,  Y10T408/05 ,  Y10T408/175 ,  Y10T409/107632

Abstract: The axis of rotation of a gear wheel subjected to thermal treatment and comprising at least one intermediate crown wheel and a pair of lateral tubular hubs arranged on opposite sides of the crown wheel is restored automatically by coupling a first of the hubs to a head rotating about a fixed axis of own rotation axis, displacing the other hub in a direction transverse to the fixed axis until both of the hubs and the crown wheel are brought into positions substantially sharing the fixed axis and providing on each of the hubs a respective centring surface sharing the fixed axis without uncoupling the first hub from the rotating head and keeping the gear wheel in a vertical and angularly fixed position.

Abstract translation: 经受热处理并包括至少一个中间冠轮和布置在冠轮相对侧上的一对横向管状轮毂的齿轮的旋转轴线通过将第一轮毂联接到围绕 固定的自身旋转轴的轴线，沿着横向于固定轴线的方向移动另一个轮毂，直到两个轮毂和冠轮被置于基本上共享固定轴线的位置，并且在每个轮毂上提供相应的定心表面共享 固定轴线，而不使第一轮毂与旋转头部分离，并将齿轮保持在垂直和角度固定的位置。

公开(公告)号：US20140341713A1

公开(公告)日：2014-11-20

申请号：US14279753

申请日：2014-05-16

Applicant: GE AVIO S.r.l.

Inventor： Davide TORZO ,  Ennio SPANO

IPC: F01D1/04 ,  F01D9/02 ,  F01D25/24

CPC classification number: F01D1/04 ,  F01D9/02 ,  F01D9/04 ,  F01D25/24 ,  F02C7/24 ,  F02K1/827 ,  F05D2220/3215 ,  F05D2230/60 ,  F05D2260/96 ,  F05D2260/961 ,  Y10T29/49245

Abstract: A low pressure turbine, in particular for a gas turbine engine, extends along an axis, has an annular conduit for guiding a gas flow and is provided with a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of the stator arrays, considering the advancement direction of the gas flow, has a plurality of blades, which define a plurality of spaces between them in circumferential direction; the spaces are split by respective splitters into a radially outer conduit and into a radially inner conduit; the radial position of the splitters is in the neighborhood of a radial reference position such that at least one acoustic mode is of the cut-on type in the radially inner conduit.

Abstract translation: 特别是用于燃气涡轮发动机的低压涡轮机沿着轴线延伸，具有用于引导气流的环形导管，并且设置有多个叶片的定子阵列和多个叶片的转子阵列; 考虑到气流的前进方向，最后的定子排列具有多个叶片，它们在圆周方向上在它们之间限定多个空间; 空间由相应的分离器分裂成径向外部管道并进入径向内部管道; 分离器的径向位置在径向参考位置附近，使得至少一个声学模式在径向内部管道中具有切割型。

公开(公告)号：US20250146442A1

公开(公告)日：2025-05-08

申请号：US18802001

申请日：2024-08-13

Applicant: GE Avio S.r.l.

Inventor： Vincenzo Martina ,  Lucia Azzini ,  Daniele Coutandin

IPC: F02C7/18 ,  B64D27/33 ,  B64D33/08 ,  F02C7/22

Abstract: An aircraft system is provided. The aircraft system includes: a gas turbine engine; a fuel system having a fuel tank and a fuel delivery system fluidly connecting the fuel tank to the gas turbine engine; an electric drive assembly including a component module; and a thermal management system including: a thermal fluid loop; a heat source heat exchanger in thermal communication with the component module and the thermal fluid loop; an airflow heat sink heat exchanger in thermal communication with the thermal fluid loop and further configured to be in thermal communication with a cooling airflow during operation of the gas turbine engine; and a fuel heat sink heat exchanger in selective thermal communication with the thermal fluid loop, the fuel tank, or both, the fuel heat sink heat exchanger in fluid communication with the fuel tank independently of the fuel delivery system during at least a first operating condition.

公开(公告)号：US20250101919A1

公开(公告)日：2025-03-27

申请号：US18976748

申请日：2024-12-11

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

Inventor： Daniel Alan Niergarth ,  Jorge de Luis ,  Douglas Downey Turner ,  Michael Macrorie ,  Keith W. Wilkinson ,  Arthur William Sibbach ,  Vincenzo Martina

IPC: F02C6/06 ,  F02C7/18

Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 ⁢ 0 - 1 ⁢ 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

公开(公告)号：US20250101916A1

公开(公告)日：2025-03-27

申请号：US18972172

申请日：2024-12-06

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

Inventor： Bugra H. Ertas ,  Xiaohua Zhang ,  Miriam Manzoni ,  Flavia Turi ,  Andrea Piazza ,  Arthur W. Sibbach ,  Brandon W. Miller

IPC: F02C7/06 ,  F16H57/04 ,  F16N7/38

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, inclusive of the endpoints. The lubricant extraction volume ratio defined by: V G V G ⁢ B · V G is a gutter volume of the gutter and VGB is a gearbox volume. The gas turbine engine includes a lubricant flow control system that includes a variable flow lubricant pump that generates a pump variable flow of lubricant to the gearbox assembly. The gearbox assembly has a variable consumption demand for delivery of lubricant. A lubricant flow controller is configured to generate a pump control command for the variable flow lubricant pump to produce the pump variable flow of lubricant based on the variable consumption demand.

公开(公告)号：US20250101911A1

公开(公告)日：2025-03-27

申请号：US18972209

申请日：2024-12-06

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

Inventor： Bugra H. Ertas ,  Xiaohua Zhang ,  Miriam Manzoni ,  Flavia Turi ,  Andrea Piazza ,  Arthur W. Sibbach

IPC: F02C3/30 ,  F02C7/06 ,  F16H57/04

Abstract: A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly 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, inclusive of the endpoints. The lubricant extraction volume ratio defined by: V G V G ⁢ B · V G is a gutter volume of the gutter and VGB is a gearbox volume.

公开(公告)号：US12258878B2

公开(公告)日：2025-03-25

申请号：US18320564

申请日：2023-05-19

Applicant: GE Avio S.r.l.

Inventor： Pietro Molesini ,  Alberto Frezet ,  Saypen Baraggia Au Yeung

IPC: F01D25/20 ,  F01D25/12 ,  F01M5/00 ,  F01M11/00 ,  F02C7/06 ,  F16H57/04 ,  F01M1/02

Abstract: A lubricant system for supplying lubrication to a component in a turbine engine includes a lubricant reservoir, a supply line fluidly coupling the lubricant reservoir to the component in the turbine engine, a scavenge line fluidly coupling the component to the lubricant reservoir, and a bypass line fluidly coupling the supply line to the scavenge line and bypassing the component.