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公开(公告)号：US20240426316A1
公开(公告)日：2024-12-26
申请号：US18826903
申请日：2024-09-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor H. Wood , Kishore Ramakrishnan , William J. Solomon , Giridhar Jothiprasad , Aaron J. King
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. 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：US10253779B2
公开(公告)日：2019-04-09
申请号：US15234029
申请日：2016-08-11
Applicant: General Electric Company
Inventor： Jixian Yao
IPC: B64C21/06 , F04D27/00 , B64D29/00 , F02C7/042 , F02K3/062 , F04D19/00 , F04D29/053 , F04D29/52 , F02K5/00 , F04D29/54
Abstract: The present disclosure is directed to an aerodynamic inlet guide vane assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet guide vane assembly is configured for mounting to fan shaft and a nacelle of the aft fan. The inlet guide vane assembly includes a plurality of inlet guide vanes grouped into a plurality of inlet guide vane groups. Each of the inlet guide vanes has a shape and an orientation corresponding to airflow conditions entering the fan. Further, the inlet guide vane groups are spaced circumferentially around the central axis as a function of the airflow conditions entering the fan.
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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：US20240295224A1
公开(公告)日：2024-09-05
申请号：US18656056
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan blades include a composite blade including a composite airfoil section having an airfoil leading edge and an airfoil trailing edge, a root attached to the composite airfoil section, and a blade shank therebetween. A metallic leading edge shield covers an axially extending portion of the composite airfoil section including at least a portion of the airfoil leading edge and covers a radially and chordwise extending portion of the airfoil leading edge of the blade shank. 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：US20240288002A1
公开(公告)日：2024-08-29
申请号：US18656067
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The annular casing is formed at least partially of a composite material. 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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Patent Agency Ranking
公开(公告)号：US11447259B2
公开(公告)日：2022-09-20
申请号：US16450131
申请日：2019-06-24
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.
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公开(公告)号：US20180057182A1
公开(公告)日：2018-03-01
申请号：US15794648
申请日：2017-10-26
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64D29/04 , B64C1/16 , B64C21/06 , B64D27/20 , B64D33/02 , B64D2033/0226 , Y02T50/166
Abstract: An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.
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公开(公告)号：US20170369152A1
公开(公告)日：2017-12-28
申请号：US15191586
申请日：2016-06-24
Applicant: General Electric Company
Inventor： Jixian Yao , Andrew Breeze-Stringfellow
CPC classification number: B64D27/20 , B64C1/26 , B64C5/02 , B64C7/02 , B64C21/00 , B64D27/12 , B64D27/14 , B64D27/18 , B64D27/26 , B64D2033/0226
Abstract: The present disclosure is directed to an aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft. For example, the stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. As such, the inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.
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公开(公告)号：US09637217B2
公开(公告)日：2017-05-02
申请号：US14859549
申请日：2015-09-21
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64C1/16 , B64C21/06 , B64C2230/00 , B64D27/14 , B64D27/20 , B64D29/00 , B64D29/04 , B64D33/02 , F02K3/04 , F05D2220/76 , Y02T50/166
Abstract: An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.
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公开(公告)号：US20240418180A1
公开(公告)日：2024-12-19
申请号：US18813567
申请日：2024-08-23
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor H. Wood , Kishore Ramakrishnan , William J. Solomon , Giridhar Jothiprasad , Aaron J. King
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. 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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