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公开(公告)号：US20180093776A1
公开(公告)日：2018-04-05
申请号：US15281990
申请日：2016-09-30
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Patrick Michael Marrinan
CPC classification number: B64D29/04 , B64D27/08 , B64D27/14 , B64D27/18 , B64D27/20 , B64D27/24 , B64D2027/026
Abstract: An aircraft includes a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage, the aft engine defining a centerline. The aft engine further includes a nacelle having a bottom section, the bottom section having a forward lip. The forward lip of the bottom section defines a camber line. The camber line, in turn, defines an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees.
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公开(公告)号：US20180051716A1
公开(公告)日：2018-02-22
申请号：US15241137
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko , Kishore Ramakrishnan , Brandon Wayne Miller
IPC: F04D29/58 , B64D27/24 , B64D33/08 , B64D29/00 , B64C21/06 , B64C5/00 , F04D19/00 , F04D25/06 , F04D29/52 , F04D29/54 , H02K7/18
CPC classification number: F04D29/5806 , B64C21/06 , B64C2230/04 , B64D27/20 , B64D27/24 , B64D29/04 , B64D33/02 , B64D33/08 , B64D33/10 , B64D2027/026 , F04D25/02 , F04D25/06 , F05B2220/303 , F05B2220/706 , H02K7/14 , H02K7/1823 , H02K9/19
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted at an aft end of the aircraft. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis, the fan driven by the electric motor. The electric propulsion system additionally includes a cooling system operable with an airflow over the aft end the aircraft when the electric propulsion system is mounted to the aircraft. The cooling system is configured to cool the electric motor during operation of the electric propulsion engine.
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公开(公告)号：US20170225773A1
公开(公告)日：2017-08-10
申请号：US15429829
申请日：2017-02-10
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan , Davide Giacché
CPC classification number: B64C21/10 , B64C3/10 , B64C3/16 , B64C2230/14 , B64D27/12 , Y02T50/166
Abstract: An apparatus configured to reduce acoustic interactions between a propeller and a surface of an aircraft positioned downstream of the propeller includes a surface modification element of the surface of the aircraft. The surface modification element defines a modified contour of the surface. The modified contour is configured to decorrelate a phase distribution of a plurality of sound sources within a source field positioned on at least a portion of the surface.
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公开(公告)号：US09725155B2
公开(公告)日：2017-08-08
申请号：US14984758
申请日：2015-12-30
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Trevor Wayne Goerig , Trevor Howard Wood , Kishore Ramakrishnan , Andrew Breeze-Stringfellow
Abstract: An aircraft and method of operating the aircraft are provided. The aircraft includes a fuselage including a nose, a tail, and a hollow, elongate body extending therebetween, a wing extending laterally away from the fuselage, the wing including a leading edge in a direction of motion of the aircraft during normal flight and a trailing edge on an opposing edge of the wing, and an engine configured to drive a bladed rotatable member, the engine coupled to at least one of the wing and the fuselage. The aircraft further includes at least one of a forward chine member and an aft chine member extending from the fuselage at a point forward of the engine aftward to a point aft of the bladed rotatable member.
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公开(公告)号：US20170175627A1
公开(公告)日：2017-06-22
申请号：US14977854
申请日：2015-12-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Howard Wood , Davide Giacché , Kishore Ramakrishnan
Abstract: A turboprop assembly includes a nacelle with a main nacelle body and a nacelle extension coupled to the main nacelle body. The nacelle extension has a wall that defines an air intake port. The air intake port has a non-circular, non-rectangular, and non-oval shaped perimeter extending in two of three dimensions.
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Patent Agency Ranking
66.发明授权公开(公告)号：US12228053B1
公开(公告)日：2025-02-18
申请号：US18232026
申请日：2023-08-09
Applicant: General Electric Company
Inventor： Trevor H. Wood , Kishore Ramakrishnan , Egbert Geertsema
Abstract: A turbofan engine and an outlet guide vane structure for the turbofan engine is provided. The outlet guide vane structure includes a non-uniform plurality of outlet guide vanes utilized in a bypass duct and between a radially inward wall and a radially outward wall. The non-uniform plurality of outlet guide vanes have varying chord lengths at the base of the outlet guide vanes along the radially inward wall. The non-uniform plurality of outlet guide vanes may include structural outlet guide vanes, non-structural outlet guide vanes, and cut-out outlet guide vanes. The non-uniform plurality of outlet guide vanes include at least one outlet guide vane integrated with a pylon and/or a bifurcation of the turbofan engine. The cut-out outlet guide vane may be integrated with the pylon and/or bifurcation. The cut-out may include a leading edge and a trailing edge disposed in front of a leading edge of the pylon.
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67.发明申请公开(公告)号：US20250052163A1
公开(公告)日：2025-02-13
申请号：US18232026
申请日：2023-08-09
Applicant: General Electric Company
Inventor： Trevor H. Wood , Kishore Ramakrishnan , Egbert Geertsema
Abstract: A turbofan engine and an outlet guide vane structure for the turbofan engine is provided. The outlet guide vane structure includes a non-uniform plurality of outlet guide vanes utilized in a bypass duct and between a radially inward wall and a radially outward wall. The non-uniform plurality of outlet guide vanes have varying chord lengths at the base of the outlet guide vanes along the radially inward wall. The non-uniform plurality of outlet guide vanes may include structural outlet guide vanes, non-structural outlet guide vanes, and cut-out outlet guide vanes. The non-uniform plurality of outlet guide vanes include at least one outlet guide vane integrated with a pylon and/or a bifurcation of the turbofan engine. The cut-out outlet guide vane may be integrated with the pylon and/or bifurcation. The cut-out may include a leading edge and a trailing edge disposed in front of a leading edge of the pylon.
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公开(公告)号：US12162221B2
公开(公告)日：2024-12-10
申请号：US17232434
申请日：2021-04-16
Applicant: General Electric Company , Concept Laser GmbH
Inventor： Eric Edward Halla , Ramakrishna Venkata Mallina , Kishore Ramakrishnan , Shashwat Swami Jaiswal , Mohammed Mounir Shalaby , Peter Pontiller-Schymura
IPC: B29C64/371 , B22F10/28 , B22F10/322 , B22F12/70 , B29C64/153 , B33Y10/00 , B33Y30/00 , B33Y40/00
Abstract: A build unit for additively manufacturing three-dimensional objects may include an energy beam system having one or more irradiation devices respectively configured to direct one or more energy beams onto a region of a powder bed, and an inertization system including an irradiation chamber defining an irradiation plenum, one or more supply manifolds, and a return manifold. The one or more supply manifolds may include a downflow manifold configured to provide a downward flow of a process gas through at least a portion of the irradiation plenum, and/or a crossflow manifold configured to provide a lateral flow of the process gas through at least a portion of the irradiation plenum. The return manifold may evacuate process gas from the irradiation plenum. While irradiating the region of the powder bed, the process gas may flow through the one or more supply manifolds, into the irradiation plenum, and into the return manifold.
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公开(公告)号：US20240318661A1
公开(公告)日：2024-09-26
申请号：US18678321
申请日：2024-05-30
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Aaron J. King
CPC classification number: F04D29/384 , F04D19/002
Abstract: A gas turbine engine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, a core turbine engine drivingly coupled to the fan and comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, and a variable bleed assembly comprising a variable bleed duct extending between a VB inlet and a VB outlet. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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公开(公告)号：US20240309828A1
公开(公告)日：2024-09-19
申请号：US18182613
申请日：2023-03-13
Applicant: General Electric Company
Inventor： Thomas Malkus , Trevor Howard Wood , Kishore Ramakrishnan
IPC: F02K1/06
CPC classification number: F02K1/06
Abstract: A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.
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