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    COMPRESSOR END-WALL TREATMENT WITH MULTIPLE FLOW AXES
    2.
    发明申请
    COMPRESSOR END-WALL TREATMENT WITH MULTIPLE FLOW AXES 审中-公开
    压缩机端面处理多个流量轴

    公开(公告)号：US20160153360A1

    公开(公告)日：2016-06-02

    申请号：US14556315

    申请日：2014-12-01

    Applicant: General Electric Company

    Inventor： Giridhar Jothiprasad ,  Ramakrishna Venkata Mallina ,  John David Stampfli ,  Rudolf Konrad Selmeier ,  Davide Giacché

    IPC: F02C7/28 ,  F04D29/40 ,  F02C3/04 ,  F04D19/02

    CPC classification number: F04D29/403 ,  F01D5/143 ,  F01D5/145 ,  F01D25/24 ,  F04D29/526 ,  F04D29/685 ,  Y02T50/673

    Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.

    Abstract translation: 提供一种压缩机，其包括壳体，轮毂，流路，多个叶片，以及形成在壳体和轮毂中的至少一个中并面向每个叶片的尖端的端壁处理。 流路形成在壳体和轮毂之间，多个叶片位于流路中。 每个叶片的尖端和端壁处理被配置为相对于彼此移动。 这种端壁处理包括沿着第一轴线延伸的第一凹部，以保持流体流动基本上直线穿过第一凹部。 端壁处理还包括多个彼此间隔开的第二凹部，并且沿着与第一轴不同的第二轴从第一凹部延伸，以保持流体流动基本上直线穿过多个第二凹部。

    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN
    4.
    发明申请
    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN 审中-公开

    公开(公告)号：US20190161167A1

    公开(公告)日：2019-05-30

    申请号：US15860280

    申请日：2018-01-02

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Davide Giacché ,  Angela Knepper ,  Nicholas Bown ,  Rathakrishnan Bhaskaran

    IPC: B64C11/18 ,  B64D33/02 ,  B64C11/14

    Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

    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。

    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN
    6.
    发明申请
    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN 有权

    公开(公告)号：US20210147065A1

    公开(公告)日：2021-05-20

    申请号：US17108431

    申请日：2020-12-01

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Davide Giacché ,  Angela Knepper ,  Nicholas Bown ,  Rathakrishnan Bhaskaran

    IPC: B64C11/18 ,  B64D33/02 ,  B64C11/14

    Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

    AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN
    9.
    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。

    Systems and methods for improved propeller design
    10.
    发明授权
    Systems and methods for improved propeller design 有权

    公开(公告)号：US11040767B2

    公开(公告)日：2021-06-22

    申请号：US15860280

    申请日：2018-01-02

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Davide Giacché ,  Angela Knepper ,  Nicholas Bown ,  Rathakrishnan Bhaskaran

    IPC: B64C11/18 ,  B64D33/02 ,  B64C11/14 ,  F02C7/04

    Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

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