公开(公告)号：US11414994B2

公开(公告)日：2022-08-16

申请号：US16988833

申请日：2020-08-10

Applicant: GE Avio S.r.l.

Inventor： Andrea Depalma ,  Antonio Giuseppe D'Ettole ,  Matteo Renato Usseglio

IPC: F01D5/06 ,  F02C3/06

Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. The rotatable annular outer drum rotor is constructed of, at least, a first drum segment and a second drum segment. The turbomachine further includes a retaining ring arranged and secured between the first and second drum segments of the rotatable annular outer drum rotor for radially retaining each of the first plurality of blades via their respective blade root portions within the rotatable annular outer drum rotor.

公开(公告)号：US11408355B2

公开(公告)日：2022-08-09

申请号：US17150136

申请日：2021-01-15

Applicant: GE Avio S.r.l.

Inventor： Juraj Hrubec ,  Davide Lauria

IPC: F02C7/06 ,  F02C7/36

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.

公开(公告)号：US11332234B2

公开(公告)日：2022-05-17

申请号：US16973268

申请日：2019-06-28

Applicant: GE Avio S.r.l.

Inventor： Pierpaolo Forte ,  Giuseppe Donini ,  Cristian Lai

IPC: B64C11/44 ,  B64C11/38 ,  B64D27/10 ,  B64D37/00 ,  F15B15/08 ,  G05D13/62 ,  F15B15/20

Abstract: A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (Ic), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (ep), the position error (ep) being a difference between a reference position (Posref) and a measured position (Posmeas) of the electro-hydraulic servo-actuator (26); and a limitation stage (58), coupled to the controller (55) to provide a limitation of the actuator speed of the electro-hydraulic servo-actuator (26); the limitation stage (58) limits a rate of change of a driving current (Id) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.

公开(公告)号：US20220145801A1

公开(公告)日：2022-05-12

申请号：US17474156

申请日：2021-09-14

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

Inventor： Nathan Evan McCurdy Gibson ,  David Justin Brady ,  Justin Paul Smith ,  Mirko Gernone

IPC: F02C7/224 ,  F02C3/22

Abstract: A fuel system for a vehicle having an engine is provided. The fuel system including: a fuel tank for holding a hydrogen fuel in a liquid phase; a fuel delivery assembly extending from the fuel tank to the engine for providing the hydrogen fuel from the fuel tank to the engine; a vaporizer in communication with the fuel delivery assembly for heating the hydrogen fuel in the liquid phase to a gaseous phase, to a supercritical phase, or both; and a high pressure pump in fluid communication with the fuel delivery assembly at a location downstream of the vaporizer for inducing a flow of the hydrogen fuel through the fuel delivery assembly to the engine.

公开(公告)号：US20220136402A1

公开(公告)日：2022-05-05

申请号：US17498090

申请日：2021-10-11

Applicant: GE Avio S.r.l. ,  GENERAL ELECTRIC COMPANY

Inventor： Mehdi M. Baladi ,  Paul Robert Gemin

IPC: F01D15/12

Abstract: A turbine engine with a turbine core that includes a compressor section having a compressor coupled to a high speed shaft, a combustion section, a turbine section having a high pressure turbine coupled to the high speed shaft and a low pressure turbine coupled to a low speed shaft, and a nozzle section. The turbine engine also includes an electric machine that can operate in a first starting mode and a second generating mode.

公开(公告)号：US11306812B2

公开(公告)日：2022-04-19

申请号：US16585041

申请日：2019-09-27

Applicant: GE Avio S.r.l.

Inventor： Miriam Manzoni ,  Davide Lercara ,  Andrea Piazza

IPC: F16H57/04 ,  B64C27/12

Abstract: A gear assembly of an aircraft including an engine is generally provided. The gear assembly includes a first gear meshed with a second gear to define a gear mesh, and a walled lubricant tank defining a lubricant reservoir and a reservoir inlet opening. The reservoir inlet opening is defined adjacent to an out-of-mesh side of the gear mesh. At least a portion of lubricant from the gear mesh enters the lubricant reservoir through the reservoir inlet opening.

公开(公告)号：US20220098987A1

公开(公告)日：2022-03-31

申请号：US17388143

申请日：2021-07-29

Applicant: GE Avio S.r.l.

Inventor： Massimiliano Airaudo ,  Paolo Calza ,  Francesco Bertini ,  Matteo Renato Usseglio ,  Cristian Lizzer ,  Ernesto Sozio ,  Matteo Furfaro ,  Marco Thiene

IPC: F01D5/18 ,  F01D5/14

Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.

公开(公告)号：US11287781B2

公开(公告)日：2022-03-29

申请号：US16485031

申请日：2018-02-16

Applicant: GE Avio S.r.l.

Inventor： Simone Castellani ,  Giuseppe Donini ,  Pierpaolo Forte ,  Cristian Lai

IPC: B64C11/30 ,  F02C9/58 ,  G05B13/02 ,  F04D29/56 ,  B63H3/10 ,  B64D33/02

Abstract: An electronic control system (30) for a turbopropeller engine (1) having a gas turbine (2, 4, 5, 6) and a propeller (7), coupled to the gas turbine, the control system (10) having a propeller control unit (14) and a turbine control unit (15) to jointly control engine power output based on an input request (PLA), wherein the propeller control unit (14) has a first reference generator (16), to determine a reference propeller speed (Npref) based on the input request (PLA), and a first regulator (19), to regulate a propeller speed (Np). The propeller control unit (14) has a reference correction stage (31) to apply a correction to the reference propeller speed (Npref) and generate thereby a corrected reference propeller speed (I), and the first regulator (19) regulates the propeller speed (Np) based on the corrected reference propeller speed (I) to achieve optimized efficiency.

公开(公告)号：US11204087B2

公开(公告)日：2021-12-21

申请号：US16482011

申请日：2018-01-26

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Simone Castellani

IPC: F16H55/17 ,  F16H55/06 ,  F02C3/107 ,  G01L3/10

Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), the shaft assembly (95) defining an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20) and further wherein the fan or propeller assembly (14) includes a gearbox (45). The shaft (assembly 95) includes a coupling shaft (100) defining a plurality of coupling shaft teeth (105) extended in the axial direction, wherein each coupling shaft tooth (105) is in circumferential arrangement along the coupling shaft (100). The coupling shaft (100) includes a first material (103) and the plurality of coupling shaft teeth (105) include a second material (104) different from the first material (103).

公开(公告)号：US11199138B2

公开(公告)日：2021-12-14

申请号：US16482024

申请日：2018-01-24

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini

IPC: F02C7/32 ,  F16C19/26 ,  F16C33/58 ,  F16C35/063 ,  F16D1/06 ,  F01D5/02 ,  F02C7/36

Abstract: A turbine engine defines an axial direction and a radial direction and includes a shaft assembly, a fan or propeller assembly, an engine core, a coupling shaft, a spacer, a sleeve, and a nut The coupling shaft defines an annular surface extended along the axial direction and a groove extended in a circumferential direction. The spacer defines a first portion disposed in the groove of the coupling shaft. The sleeve defines a threaded portion that extends along the axial direction and is disposed outward of the spacer in the radial direction. The nut defines a plurality of nut threads configured to mate with the plurality of sleeve threads of the sleeve. The nut defines a radial portion adjacent to at least a portion of the sleeve and at least a portion of the spacer in the axial direction.