公开(公告)号：US20250129756A1

公开(公告)日：2025-04-24

申请号：US18975350

申请日：2024-12-10

Applicant: General Electric Company

Inventor： Randy M. Vondrell ,  Alexander Kimberley Simpson ,  David Marion Ostdiek ,  Craig William Higgins

IPC: F02K3/065 ,  F02C3/06

Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct, a primary fan driven by the turbomachine, a secondary fan located downstream of the primary fan within the inlet duct, and a booster located downstream of the secondary fan and comprising a booster rotor blade, an inlet guide vane, and booster cowl, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet, the inlet guide vane located forward of the booster rotor blade.

公开(公告)号：US12270340B2

公开(公告)日：2025-04-08

申请号：US18404364

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: F02C7/22 ,  H01M8/04089 ,  H01M8/04111 ,  H01M8/0612

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 and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly having a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both.

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.