公开(公告)号：US12261334B2

公开(公告)日：2025-03-25

申请号：US18404083

申请日：2024-01-04

Applicant: General Electric Company

Inventor： Honggang Wang ,  Brandon Wayne Miller ,  Michael Anthony Benjamin ,  Richard L. Hart ,  Randy M. Vondrell ,  Ryan St. Pierre

IPC: H01M8/0612 ,  F02C7/22

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.

公开(公告)号：US20240426249A1

公开(公告)日：2024-12-26

申请号：US18824100

申请日：2024-09-04

Applicant: General Electric Company

Inventor： Daniel John Oehrle ,  Randy M. Vondrell

IPC: F02C7/32 ,  B64D27/12

Abstract: A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.

公开(公告)号：US20240352866A1

公开(公告)日：2024-10-24

申请号：US18354021

申请日：2023-07-18

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

Inventor： Randy M. Vondrell ,  Kevin William Caldwell ,  John Carl Glessner ,  Javier Barba Fuentes ,  Dorota Kopkowicz

IPC: F01D11/20 ,  F02C9/20

CPC classification number: F01D11/20 ,  F05D2260/213

Abstract: A gas turbine engine includes a fan section, an engine inlet, and a fan duct splitter in serial flow order. The fan duct splitter splits an airflow entering the engine inlet from the fan section into a fan duct and a core duct. The core duct includes a compressor section, a combustion section, and a turbine section in serial flow order. A duct assembly is coupled to the fan duct to extract a portion of a fan duct airflow passing through the fan duct and deliver the portion of the fan duct airflow to an active clearance control mechanism of the turbine section.

公开(公告)号：US11685542B2

公开(公告)日：2023-06-27

申请号：US16891337

申请日：2020-06-03

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Randy M. Vondrell ,  Brandon Wayne Miller ,  Patrick Michael Marrinan ,  Lawrence Chih-Hui Cheung ,  Nikolai N. Pastouchenko

IPC: B64D27/10 ,  B64D27/24 ,  B64D33/08 ,  F02K5/00 ,  F02C7/14 ,  F02C6/20 ,  B64C11/00 ,  B64C21/06 ,  F01D15/10 ,  F01D15/12 ,  F02K3/062 ,  F04D29/056 ,  F04D29/063 ,  F04D29/32 ,  F04D29/58 ,  B64D27/02

CPC classification number: B64D33/08 ,  B64C11/001 ,  B64C21/06 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F01D15/12 ,  F02C6/206 ,  F02C7/14 ,  F02K3/062 ,  F02K5/00 ,  F04D29/056 ,  F04D29/063 ,  F04D29/325 ,  F04D29/582 ,  B64D2027/026 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/98 ,  Y02T50/60

Abstract: A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.

公开(公告)号：US20220289394A1

公开(公告)日：2022-09-15

申请号：US17571752

申请日：2022-01-10

Applicant: General Electric Company

Inventor： Thomas Kupiszewski ,  Brandon Wayne Miller ,  Daniel Alan Niergarth ,  Randy M. Vondrell

IPC: B64D27/24 ,  F01D15/10 ,  F01D25/18 ,  F02K5/00 ,  F04D25/06 ,  F02C7/32 ,  B64D27/12 ,  F02C7/24 ,  F02K3/06 ,  F04D19/02 ,  H02K1/27 ,  H02K7/18

Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.

公开(公告)号：US11156128B2

公开(公告)日：2021-10-26

申请号：US16108732

申请日：2018-08-22

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Randy M. Vondrell ,  Darek Tomasz Zatorski ,  Christopher Charles Glynn

IPC: F01D25/28 ,  B64D27/10 ,  F01D15/10 ,  B64D27/02

Abstract: A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.

公开(公告)号：US20190023408A1

公开(公告)日：2019-01-24

申请号：US15699349

申请日：2017-09-08

Applicant: General Electric Company

Inventor： Kurt David Murrow ,  Darek Tomasz Zatorksi ,  Andrew Breeze-Stringfellow ,  Randy M. Vondrell ,  Dominic Barone

IPC: B64D27/08 ,  B64D27/24 ,  B64C3/32 ,  B64C29/00 ,  B64C11/30 ,  B64C27/26 ,  B64D35/02

Abstract: An aircraft includes a fuselage; a wing coupled to, and extending from, the fuselage; and a hybrid-electric propulsion system. The hybrid-electric propulsion system includes a power source including a combustion engine and an electric generator; a plurality of vertical thrust electric fans integrated into the wing and oriented to generate thrust along the vertical direction, the plurality of vertical thrust electric fans arranged along a length of the wing and driven by the power source; and a forward thrust propulsor. The forward thrust propulsor it is selectively or permanently mechanically coupled to the combustion engine.

公开(公告)号：US20180304753A1

公开(公告)日：2018-10-25

申请号：US15493544

申请日：2017-04-21

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Anthony Austin Bouvette ,  Glenn David Crabtree

IPC: B60L11/14 ,  B64D27/12 ,  B64D27/18 ,  B64C21/06 ,  H02G5/10 ,  F02K3/04 ,  F02C6/20 ,  H02K7/18

Abstract: A propulsion system for an aircraft includes an electric power source and an electric propulsion assembly having an electric motor and a propulsor, the propulsor powered by the electric motor. The propulsion system also includes an electric power bus electrically connecting the electric power source to the electric propulsion assembly. The electric power source is configured to provide electrical power to the electric power bus, and the electric power bus is configured to transfer the electric power to the electric propulsion assembly at a voltage exceeding 800 volts.

公开(公告)号：US10093428B2

公开(公告)日：2018-10-09

申请号：US15242844

申请日：2016-08-22

Applicant: General Electric Company

Inventor： Thomas Kupiszewski ,  Brandon Wayne Miller ,  Randy M. Vondrell

IPC: B64D27/24 ,  B60L11/06 ,  H02J1/10 ,  H02J4/00 ,  B64D27/02 ,  H02J1/00

Abstract: A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.

公开(公告)号：US20180216575A1

公开(公告)日：2018-08-02

申请号：US15417745

申请日：2017-01-27

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Matthew Ryan Polakowski ,  Patrick Michael Marrinan ,  Joel Francis Kirk ,  Randy M. Vondrell ,  Jeffrey Donald Clements

IPC: F02K3/06 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C7/36

CPC classification number: F02K3/06 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C7/36 ,  F05D2220/36 ,  F05D2300/20 ,  Y02T50/672

Abstract: A turbofan engine is provided including a fan having a plurality of rotatable fan blades and defining a fan pressure ratio during operation of the turbofan engine. The turbofan engine also includes a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath. The turbofan also includes an outer nacelle at least partially surrounding the fan and the turbomachine, the outer nacelle defining a bypass passage with the turbomachine. A bypass ratio of an amount of airflow through the bypass passage to an amount of airflow through the core air flowpath during operation of the turbofan is less than or equal to about 11 and wherein the fan pressure ratio is less than or equal to about 1.5.