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：US11713721B1

公开(公告)日：2023-08-01

申请号：US17929542

申请日：2022-09-02

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

Inventor： Andrea Piazza ,  Jeffrey D. Clements

IPC: F02C7/36 ,  F02C3/067 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02C3/067 ,  F02K3/06 ,  F05D2200/13 ,  F05D2200/14 ,  F05D2200/221 ,  F05D2260/40311 ,  F05D2260/98

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox 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 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.

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.

公开(公告)号：US20220364636A1

公开(公告)日：2022-11-17

申请号：US17488784

申请日：2021-09-29

Applicant: GE Avio S.r.l.

Inventor： Lucia Azzini ,  Fabio De Bellis ,  Andrea Piazza

IPC: F16H55/06 ,  F16H1/28 ,  F16H57/08 ,  F02C7/36 ,  C23C16/50 ,  C23C16/26 ,  C23C16/30 ,  C23C16/34 ,  C23C24/04

Abstract: A component includes a metallic substrate having a tribological surface and a coating. The coating includes a first layer disposed on the tribological surface and a second layer disposed on the first layer. The first layer includes titanium, chromium, or a diamond-like carbon (DLC). The second layer includes a disulfide.

公开(公告)号：US20220325669A1

公开(公告)日：2022-10-13

申请号：US17581057

申请日：2022-01-21

Applicant: GE Avio S.r.l.

Inventor： Andrea Piazza

IPC: F02C7/36 ,  F02C7/06

Abstract: A gear assembly comprises a plurality of planet gear layshafts that have an outer surface having a plurality of gear surfaces and a surface having one or more bearing surfaces. The one or more bearing surfaces of the surfaces of the planet gear layshafts have a first case hardening depth and a first nitriding hardness depth. The gear surfaces of the outer surface of the planet gear layshafts have a second case hardening depth.

公开(公告)号：US11434765B2

公开(公告)日：2022-09-06

申请号：US17148635

申请日：2021-01-14

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

Inventor： Ernesto Sozio ,  Francesco Bertini ,  Jeffrey Donald Clements ,  Jonathan Ong ,  Lyle Douglas Dailey ,  Paul Hadley Vitt ,  Matteo Renato Usseglio

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/54

Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).