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    Aircraft having an aft engine
    3.
    发明授权
    Aircraft having an aft engine 有权

    公开(公告)号：US11299283B2

    公开(公告)日：2022-04-12

    申请号：US16512730

    申请日：2019-07-16

    Applicant: General Electric Company

    Inventor： Kishore Ramakrishnan ,  Jixian Yao ,  Nikolai N. Pastouchenko ,  Ivan Malcevic

    IPC: B64D27/14 ,  B64C21/00 ,  B64D27/20 ,  B64C5/06 ,  B64C1/16 ,  B64C21/08 ,  B64C1/00

    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.

    CIRCUMFERENTIALLY VARYING AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN
    5.
    发明申请
    CIRCUMFERENTIALLY VARYING AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN 审中-公开
    循环式轴流式压缩机终端处理，用于控制泄漏流量

    公开(公告)号：US20160169017A1

    公开(公告)日：2016-06-16

    申请号：US14572119

    申请日：2014-12-16

    Applicant: General Electric Company

    Inventor： Davide Giacché ,  John David Stampfli ,  Ramakrishna Venkata Mallina ,  Vittorio Michelassi ,  Giridhar Jothiprasad ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier ,  Sungho Yoon ,  Ivan Malcevic

    IPC: F01D11/00 ,  F02C3/04

    CPC classification number: F01D11/001 ,  F04D27/02 ,  F04D29/526 ,  F04D29/68 ,  F04D29/681 ,  F04D29/685

    Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

    Abstract translation: 一种用于燃气涡轮发动机的压缩机，其包括用于控制压缩机中的泄漏流动和周向流动不均匀性的一个或多个端壁处理。 压缩机包括壳体，毂，形成在壳体和轮毂之间的流动路径，位于流动路径中的多个叶片，以及形成在至少一个的内表面中的一个或多个周向变化的端壁处理 套管或轮毂。 一个或多个周向变化的端壁处理中的每一个基于它们与紧邻的上游bladerow的相对位置周向地变化。 一个或多个端壁处理中的每一个在相对于直接相邻的上游bladerow的放置中的至少一个中或在限定多个周向变化的端壁处理中的每一个的几何参数中的周向变化。 另外公开了一种包括压缩机的发动机。

    Aircraft having an aft engine and internal flow passages
    6.
    发明授权
    Aircraft having an aft engine and internal flow passages 有权

    公开(公告)号：US10399670B2

    公开(公告)日：2019-09-03

    申请号：US15275610

    申请日：2016-09-26

    Applicant: General Electric Company

    Inventor： Nikolai N. Pastouchenko ,  Ivan Malcevic

    IPC: B64C21/04 ,  B64C21/06 ,  B64D27/20

    Abstract: An air injection assembly for an aircraft is provided. The aircraft includes a fuselage extending between a forward end and an aft end along a longitudinal direction and a boundary layer ingestion fan mounted to the fuselage at the aft end of the fuselage. The air injection assembly includes a plurality of injection ports defined on a surface of the fuselage at a location upstream of the boundary layer ingestion fan. A supplemental airflow is provided through a fluid passageway to the injection ports where it is ejected to displace at least a portion of relatively higher velocity boundary layer airflow. In this manner, the airflow entering boundary layer ingestion fan is more uniform, has less swirl distortion, and has a lower average velocity.

    Aircraft having an aft engine and stabilizer root fillet
    7.
    发明授权
    Aircraft having an aft engine and stabilizer root fillet 有权

    公开(公告)号：US10364021B2

    公开(公告)日：2019-07-30

    申请号：US15275901

    申请日：2016-09-26

    Applicant: General Electric Company

    Inventor： Nikolai N. Pastouchenko ,  Ivan Malcevic

    IPC: B64D27/20 ,  B64C21/02 ,  B64C5/02 ,  B64C1/16 ,  B64C1/26 ,  B64C21/06

    Abstract: An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A stabilizer assembly and 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 stabilizer assembly includes a stabilizer and a root fillet extending between the stabilizer and the fuselage. The root fillet defines a flow directing surface configured for urging a flow of boundary layer air upward along the vertical direction. In addition, an airflow modifying element may protrude from a surface of the fuselage or the root fillet, the airflow modifying element being configured for directing or reducing swirl in the flow of boundary layer air.

    AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN
    8.
    发明申请
    AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN 审中-公开
    用于控制泄漏流量的轴流式压缩机末端处理

    公开(公告)号：US20160153465A1

    公开(公告)日：2016-06-02

    申请号：US14556452

    申请日：2014-12-01

    Applicant: General Electric Company

    Inventor： Sungho Yoon ,  John David Stampfli ,  Ramakrishna Venkata Mallina ,  Vittorio Michelassi ,  Giridhar Jothiprasad ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier ,  Davide Giacché ,  Ivan Malcevic

    IPC: F04D29/52 ,  F02C3/04 ,  F01D11/08

    CPC classification number: F04D29/526 ,  F04D29/321 ,  F04D29/522 ,  F04D29/685

    Abstract: An axial compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow in the compressor. The one or more endwall treatments having a height formed in an interior surface of a compressor casing or a compressor hub and configured to return a flow adjacent a plurality of rotor blade tips or a plurality of stator blade tips to a cylindrical flow passage upstream of a point of removal of the flow. Each of the endwall treatments defining a front wall, a rear wall, an outer wall extending between the front wall and the rear wall, an axial overhang, an axial overlap, an axial lean angle and a tangential lean angle. The axial overhang extending upstream to overhang at least one of the at least one set of rotor blades or the at least one set of stator blades. The axial overlap extending downstream to overlap at least one of the at least one set of rotor blades or the at least one set of stator blades.

    Abstract translation: 一种用于燃气涡轮发动机的轴向压缩机，包括用于控制压缩机中的泄漏流的一个或多个端壁处理。 所述一个或多个端壁处理具有形成在压缩机壳体或压缩机毂的内表面中的高度，并且被配置为将邻近多个转子叶片尖端或多个定子叶片尖端的流返回到一个圆柱形流动通道 清除流量点。 每个端壁处理限定了前壁，后壁，在前壁和后壁之间延伸的外壁，轴向突出，轴向重叠，轴向倾斜角和切向倾斜角。 所述轴向突出部在所述至少一组所述转子叶片或所述至少一组定子叶片中的至少一个的上游延伸。 在下游延伸的轴向重叠与所述至少一组转子叶片或至少一组定子叶片中的至少一个重叠。

    Compressor end-wall treatment having a bent profile
    9.
    发明授权
    Compressor end-wall treatment having a bent profile 有权

    公开(公告)号：US10539154B2

    公开(公告)日：2020-01-21

    申请号：US15531992

    申请日：2014-12-10

    Applicant: General Electric Company

    Inventor： Ramakrishna Venkata Mallina ,  Sungho Yoon ,  Vittorio Michelassi ,  Ivan Malcevic

    IPC: F04D29/52 ,  F02C3/04 ,  F04D29/32 ,  F04D29/54 ,  F01D5/14 ,  F01D11/08 ,  F04D29/68

    Abstract: A compressor is provided including a compressor end-wall having a casing and a hub. The compressor further includes at least one set of rotor blades, one set of stator blades, and a plurality of end-wall treatments spaced apart from each other, formed in an interior surface of at least one of the casing and hub, and facing a tip of the rotor blade or stator blade. Each end-wall treatment includes a forward recess portion extending along a first axis and an aft recess portion extending along a second axis different than the first axis. The aft recess portion is joined to the corresponding forward recess portion via an intersection portion which is inclined relative to at least one of the first axis, and the second axis. The aft recess portion and/or the forward recess portion are bent from the intersection portion and inclined relative to an axial direction of the compressor.

    Aircraft Having an Aft Engine
    10.
    发明申请
    Aircraft Having an Aft Engine 审中-公开

    公开(公告)号：US20190337630A1

    公开(公告)日：2019-11-07

    申请号：US16512730

    申请日：2019-07-16

    Applicant: General Electric Company

    Inventor： Kishore Ramakrishnan ,  Jixian Yao ,  Nikolai N. Pastouchenko ,  Ivan Malcevic

    IPC: B64D27/14 ,  B64D27/20 ,  B64C5/06 ,  B64C21/00 ,  B64C1/16 ,  B64C21/08

    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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