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公开(公告)号：US20230160312A1
公开(公告)日：2023-05-25
申请号：US17535291
申请日：2021-11-24
Applicant: General Electric Company
Inventor： Li Zheng , Scott Roger Finn , Nicholas J. Kray , Trevor H. Wood , Kishore Ramakrishnan
CPC classification number: F01D5/3007 , F01D5/282 , F05D2220/32 , F05D2240/30 , F05D2230/60
Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.
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公开(公告)号：US20220331875A1
公开(公告)日：2022-10-20
申请号：US17232516
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
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 defined by the irradiation chamber, and/or a crossflow manifold configured to provide a lateral flow of the process gas through at least a portion of the irradiation plenum defined by the irradiation chamber. The return manifold may evacuate or otherwise remove process gas from the irradiation plenum defined by the irradiation chamber. 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 from the irradiation plenum into the return manifold.
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公开(公告)号：US20220331869A1
公开(公告)日：2022-10-20
申请号：US17232467
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 , Adam Garret Susong , Peter Pontiller-Schymura
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 defined by the irradiation chamber, and/or a crossflow manifold configured to provide a lateral flow of the process gas through at least a portion of the irradiation plenum defined by the irradiation chamber. The return manifold may evacuate or otherwise remove process gas from the irradiation plenum defined by the irradiation chamber. 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 from the irradiation plenum into the return manifold.
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公开(公告)号：US11255343B2
公开(公告)日：2022-02-22
申请号：US15887340
申请日：2018-02-02
Applicant: General Electric Company
Inventor： Trevor Wood , Kishore Ramakrishnan
Abstract: A system includes an airfoil disposed inside an engine assembly that includes a pressure side and a suction side that are coupled together at a leading edge and a trailing edge. The airfoil extends a radial length away from a central axis of the engine assembly between a hub end and a tip end. The airfoil includes a sweep feature disposed at the leading edge that is shaped to alter the air inside the engine assembly. Altering the air inside the engine assembly reduces a surface unsteady pressure level on the airfoil. The system includes a fan frame assembly comprising an inner and outer surface. The hub end is coupled with the inner surface and the tip end is coupled with the outer surface. The airfoil is integrated with the fan frame assembly such that the airfoil increases a structural load supporting capability of the fan frame assembly.
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公开(公告)号：US20220025814A1
公开(公告)日：2022-01-27
申请号：US16938150
申请日：2020-07-24
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Nikolai N. Pastouchenko , Kishore Ramakrishnan , Timothy Richard DePuy , Wendy Wenling Lin , Robert William Davidoff
IPC: F02C7/045 , F02K1/82 , G10K11/172 , B32B3/12
Abstract: An acoustic core includes an array of resonant cells. The array may include a plurality of coupled resonant cells respectively defining an antecedent resonant space and a subsequent resonant space, with at least one cell wall having one or more wall-apertures defining a pathway between the antecedent resonant space and the subsequent resonant space. The array may include a plurality of high-frequency resonant cells respectively defining a high-frequency resonant space and being matched with respective ones of the plurality of coupled resonant cells. A cross-sectional dimension of the one or more wall-apertures defining the pathway between the antecedent resonant space and the subsequent resonant space may be less than a cross-sectional dimension of the antecedent resonant space and/or a cross-sectional dimension of the subsequent resonant space. The array may include a plurality of partitioned resonant cells that have a partition integrally formed with at least one of a corresponding one or more cell walls and transecting the corresponding resonant space with at least one surface of the partition having an interface angle that is oblique or perpendicular relative to a plane parallel to a top face and/or a bottom face of the array of resonant cells.
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Patent Agency Ranking
公开(公告)号：US20190176971A1
公开(公告)日：2019-06-13
申请号：US16279244
申请日：2019-02-19
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.
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公开(公告)号：US10252791B2
公开(公告)日：2019-04-09
申请号：US15244032
申请日：2016-08-23
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage extending between a forward end and an aft end. The aircraft additionally includes a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor including an outer nacelle and the outer nacelle defining an inlet. Additionally, the aircraft includes a deployable assembly attached to at least one of the fuselage or the outer nacelle, the deployable assembly movable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position to increase an efficiency of the aft fan and/or of the aircraft.
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公开(公告)号：US20180079514A1
公开(公告)日：2018-03-22
申请号：US15271776
申请日：2016-09-21
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Jixian Yao , Nikolai N. Pastouchenko , Ivan Malcevic
CPC classification number: B64D27/14 , B64C1/16 , B64C5/06 , B64C21/00 , B64C21/08 , B64C2001/0045 , B64C2230/04 , B64D27/20 , Y02T50/12 , Y02T50/166
Abstract: An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.
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公开(公告)号：US20180043996A1
公开(公告)日：2018-02-15
申请号：US15234055
申请日：2016-08-11
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan
CPC classification number: B64C21/06 , B64C2230/04 , B64D29/00 , B64D2033/0226 , F02C7/042 , F02K3/062 , F02K5/00 , F04D19/002 , F04D29/522 , F04D29/542 , F05D2220/323 , F05D2230/80 , F05D2250/51 , Y02T50/671
Abstract: The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members, such as struts or strakes, mounted at predetermined locations around a circumference of the fan shaft of the fan at the inlet. The predetermined location(s) may be determined as a function of swirl distortion entering the inlet. As such, the structural member(s) are configured to reduce swirl distortion of the airflow entering the fan. In some embodiments, the inlet assembly may also include inlet guide vanes. In alternative embodiments, the inlet assembly may be absent of inlet guide vanes.
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公开(公告)号：US20170190409A1
公开(公告)日：2017-07-06
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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