公开(公告)号：US20230374935A1

公开(公告)日：2023-11-23

申请号：US17747497

申请日：2022-05-18

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

Inventor： Paul Hadley Vitt ,  Lyle Douglas Dailey ,  Matteo Renato Usseglio ,  Andreas Peters

IPC: F02C3/067 ,  F02C6/00 ,  F02C7/36

CPC classification number: F02C3/067 ,  F02C6/00 ,  F02C7/36 ,  F05D2220/76

Abstract: A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial direction

公开(公告)号：US20230314254A1

公开(公告)日：2023-10-05

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

IPC: G01L25/00 ,  G01L5/00 ,  F02C9/00

CPC classification number: G01L25/003 ,  G01L5/00 ,  F02C9/00

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.

公开(公告)号：US20230296024A1

公开(公告)日：2023-09-21

申请号：US17951653

申请日：2022-09-23

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

Inventor： Francesco Bertini ,  Davide Torzo ,  Pratish Patil ,  John Joseph ,  Mahendran Manoharan ,  Ganesh Seshadri

IPC: F01D5/14

CPC classification number: F01D5/142 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/30

Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.

公开(公告)号：US11739643B2

公开(公告)日：2023-08-29

申请号：US17154153

申请日：2021-01-21

Applicant: GE Avio S.r.l.

Inventor： Alberto Buonvino ,  Daniele Coutandin ,  Luca Giacobone ,  Riccardo Da Soghe ,  Cosimo Bianchini

IPC: F01D5/08 ,  F02C3/067 ,  F02C6/08 ,  F01D5/03

CPC classification number: F01D5/085 ,  F02C3/067 ,  F02C6/08 ,  F01D5/03 ,  F05D2260/232 ,  F05D2260/606

Abstract: A turbine engine having counter-rotating rotors comprising a first rotor, rotating in a first rotational direction, defining a first rotor set of blades axially spaced to define a gap, and a second rotor, rotating in a second rotational direction counter the first rotational direction. The second rotor further including a second set of blades received within the gap of the first rotor. A plurality of fluid passages is formed in the first rotor with an outlet facing the gap.

公开(公告)号：US20230265797A1

公开(公告)日：2023-08-24

申请号：US17678824

申请日：2022-02-23

Applicant: General Electric Company ,  GE AVIO S.R.L

Inventor： David Justin Brady ,  Mirko Gernone ,  Nathan E Gibson

IPC: F02C7/224 ,  F02C3/22 ,  F02C3/30 ,  B64D37/32

CPC classification number: F02C7/224 ,  F02C3/22 ,  F02C3/30 ,  B64D37/32 ,  F05D2260/213 ,  F05D2260/607 ,  F05D2260/99

Abstract: Methods and apparatus to produce hydrogen gas turbine propulsion are disclosed. An example apparatus to produce propulsion in a gas turbine engine includes a fluid line to transport hydrogen from a hydrogen supply and an inert gas from an inert gas supply to a gas turbine combustor. The apparatus also includes at least one heat exchanger coupled to the fluid line to heat the inert gas and the hydrogen in the fluid line.

公开(公告)号：US20230243311A1

公开(公告)日：2023-08-03

申请号：US17590472

申请日：2022-02-01

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

Inventor： David Justin Brady ,  Mirko Gernone ,  Michael A. Benjamin ,  Steven C. Vise

IPC: F02C9/40 ,  F02C7/22 ,  F23R3/36 ,  F23R3/30

CPC classification number: F02C9/40 ,  F02C7/22 ,  F23R3/36 ,  F23R3/30 ,  F05D2220/32 ,  F05D2240/36

Abstract: A fuel supply system for a combustion section of a turbine engine. The turbine engine including a heat source. The fuel supply system comprising a first fuel supply having a liquid fuel, a second fuel supply having a first gaseous fuel, and a heat exchanger fluidly coupled to the first fuel supply and the heat source. The heat exchanger producing a heat sufficient to change the liquid fuel to a second gaseous fuel that is the same type of fuel as the first gaseous fuel.

公开(公告)号：US20230212987A1

公开(公告)日：2023-07-06

申请号：US18058034

申请日：2022-11-22

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

Inventor： Narayanan Payyoor ,  Weize Kang ,  Brandon W. Miller ,  Bugra Ertas ,  Andrea Piazza

IPC: F02C7/36 ,  F02C7/06

CPC classification number: F02C7/36 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/60 ,  F05D2260/40

Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)½ and three hundred (ft/sec)½. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.

公开(公告)号：US11649771B2

公开(公告)日：2023-05-16

申请号：US16479801

申请日：2018-01-19

Applicant: GE Avio S.r.l.

Inventor： Simone Castellani ,  Pierpaolo Forte

IPC: F02C9/58 ,  B64C19/00

CPC classification number: F02C9/58 ,  B64C19/00 ,  F05D2220/323 ,  F05D2270/021

Abstract: A control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4), is provided with: a control unit (12) to control a forward operating mode or a reverse operating mode of the gas turbine engine (1); and a supervising unit (14), operatively coupled to the control unit (12), to receive an input signal (PLA) indicative of a forward, or reverse, power request and to cause the control unit (12) to control the forward, or reverse, operating mode based on the input signal (PLA). The supervising unit (14) has an enabling stage (20) to enable a transition between the forward and reverse operating modes based on a check that a safety condition is satisfied.

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

IPC: F02C7/36 ,  F16C1/02 ,  F16D3/06 ,  F02C9/00 ,  F16H1/28 ,  F16H57/00

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.

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

IPC: F02C7/32 ,  F01D25/36 ,  F02C7/275 ,  F01D21/12 ,  F01D21/14 ,  F02C7/06

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.