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公开(公告)号：US20240239504A1
公开(公告)日：2024-07-18
申请号：US18307172
申请日：2023-04-26
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a lengthwise direction, a leading edge, a trailing edge, and a chord extending from the leading edge to the trailing edge, the pylon fairing including a maximum thickness portion along the lengthwise direction of the pylon fairing located between 10% and 60% of the chord.
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公开(公告)号：US12280883B2
公开(公告)日：2025-04-22
申请号：US18307917
申请日：2023-04-27
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan that defines a plurality of fan wakes; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a pylon fairing dihedral, wherein the pylon fairing dihedral is in a direction opposite the incoming fan flow swirl and associated sheared profiles of fan wakes upon arrival at the pylon leading edge.
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公开(公告)号：US20240239506A1
公开(公告)日：2024-07-18
申请号：US18316577
申请日：2023-05-12
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a lengthwise direction and comprising a leading edge section, the leading edge section defining a leading edge camber that varies along the lengthwise direction of the pylon fairing.
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公开(公告)号：US20240239505A1
公开(公告)日：2024-07-18
申请号：US18307917
申请日：2023-04-27
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan that defines a plurality of fan wakes; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a pylon fairing dihedral, wherein the pylon fairing dihedral is in a direction opposite the incoming fan flow swirl and associated sheared profiles of fan wakes upon arrival at the pylon leading edge.
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公开(公告)号：US20240239503A1
公开(公告)日：2024-07-18
申请号：US18307110
申请日：2023-04-26
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan defining a fan diameter; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a leading edge and including a first inflection point along the leading edge, the first inflection point defining a first radius of curvature that is less than 5 times the fan diameter and greater than 0.1 times the fan diameter.
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Patent Agency Ranking
公开(公告)号：US20240060430A1
公开(公告)日：2024-02-22
申请号：US17889927
申请日：2022-08-17
Applicant: General Electric Company
Inventor： William Joseph Bowden , Keith Edward James Blodgett
CPC classification number: F01D25/24 , F01D25/28 , F05D2220/323 , F05D2240/14 , F05D2250/72 , F05D2250/38 , F05D2260/30
Abstract: A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.
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公开(公告)号：US20240369016A1
公开(公告)日：2024-11-07
申请号：US18773663
申请日：2024-07-16
Applicant: General Electric Company
Inventor： William Joseph Bowden , Steven B. Morris , Vicente Jerez Fidalgo
Abstract: An engine includes a fan section having an open fan defining an axial centerline and a rotor. The rotor includes a plurality of fan blades mounted to a hub and being rotatable about the axial centerline. The engine also includes a turbomachine downstream of the fan section. The turbomachine includes a core cowl that defines an engine inlet and encloses turbomachinery. Further, the engine includes an airflow diverting assembly downstream of the fan section and upstream of the engine inlet. The airflow diverting assembly includes at least one fluid passageway formed into at least a portion of the hub for diverting at least a portion of a boundary layer on a surface of the hub away from the surface of the hub to reduce distortion caused by the boundary layer in the turbomachinery.
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公开(公告)号：US12055094B1
公开(公告)日：2024-08-06
申请号：US18171698
申请日：2023-02-21
Applicant: General Electric Company
Inventor： William Joseph Bowden , Steven B. Morris , Vicente Jerez Fidalgo
Abstract: An engine includes a fan section having an open fan defining an axial centerline and a rotor. The rotor includes a plurality of fan blades mounted to a hub and being rotatable about the axial centerline. The engine also includes a turbomachine downstream of the fan section. The turbomachine includes a core cowl that defines an engine inlet and encloses turbomachinery. Further, the engine includes an airflow diverting assembly downstream of the fan section and upstream of the engine inlet. The airflow diverting assembly includes at least one fluid passageway formed into at least a portion of the hub for diverting at least a portion of a boundary layer on a surface of the hub away from the surface of the hub to reduce distortion caused by the boundary layer in the turbomachinery.
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公开(公告)号：US11629651B2
公开(公告)日：2023-04-18
申请号：US16950099
申请日：2020-11-17
Applicant: General Electric Company
Inventor： William Joseph Bowden
Abstract: A gas turbine engine including: a turbomachine coupled to a propeller of the gas turbine engine, the turbomachine being in fluid communication with an external environment through an air inlet; and an electric motor coupled to the propeller, wherein the air inlet is in fluid communication with a bypass duct having a selectively variable geometry.
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公开(公告)号：US20250116243A1
公开(公告)日：2025-04-10
申请号：US18982445
申请日：2024-12-16
Applicant: General Electric Company
Inventor： William Joseph Bowden , Keith Edward James Blodgett , Mustafa Dindar , David Cerra , James Hamilton Grooms , Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberely Simpson
Abstract: A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct. The primary fan is driven by the turbomachine, and a secondary fan is located downstream of the primary fan within the inlet duct. One or more actuation devices operably associated with the fan duct, the one or more actuation devices actuable to increase or decrease an exit area of the fan duct.
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