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    CIRCUMFERENTIALLY VARYING AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN
    1.
    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。

    Airfoil shape for eighth stage compressor rotor blade
    2.
    发明授权
    Airfoil shape for eighth stage compressor rotor blade 有权

    公开(公告)号：US10443611B2

    公开(公告)日：2019-10-15

    申请号：US15277576

    申请日：2016-09-27

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： John David Stampfli ,  Nandakumar Aladahalli Rangaswamy

    IPC: F04D29/38 ,  F04D29/32 ,  F04D29/54 ,  F02C3/04 ,  F01D5/14

    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

    Compressor end-wall treatment with multiple flow axes
    3.
    发明授权
    Compressor end-wall treatment with multiple flow axes 有权

    公开(公告)号：US10823194B2

    公开(公告)日：2020-11-03

    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: F04D29/40 ,  F01D5/14 ,  F01D25/24 ,  F04D29/52 ,  F04D29/68

    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.

    Systems and Methods for Modifying a Pressure Side on an Airfoil About a Trailing Edge
    6.
    发明申请
    Systems and Methods for Modifying a Pressure Side on an Airfoil About a Trailing Edge 有权
    关于翼缘上的压力侧修改的系统和方法

    公开(公告)号：US20150075179A1

    公开(公告)日：2015-03-19

    申请号：US14031206

    申请日：2013-09-19

    Applicant: General Electric Company

    Inventor： John David Stampfli ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier

    IPC: F01D5/14

    CPC classification number: F01D5/14 ,  F01D5/141 ,  F05D2250/712 ,  F05D2250/713

    Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.

    Abstract translation: 本文公开了一种翼型件。 翼型件可以包括前缘，后缘，限定在前缘和后缘之间的吸力侧，以及限定在前缘和与吸力侧相对的后缘之间的压力侧。 压力侧可以包括围绕后缘的凹形轮廓，其与压力侧的剩余部分的轮廓不同。

    Airfoil shape for fourth stage compressor rotor blade
    7.
    发明授权
    Airfoil shape for fourth stage compressor rotor blade 有权

    公开(公告)号：US10415585B2

    公开(公告)日：2019-09-17

    申请号：US15272018

    申请日：2016-09-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： John David Stampfli ,  John David Dyer

    IPC: F04D29/32 ,  F01D5/14

    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

    AIRFOIL SHAPE FOR FOURTH STAGE COMPRESSOR ROTOR BLADE
    8.
    发明申请
    AIRFOIL SHAPE FOR FOURTH STAGE COMPRESSOR ROTOR BLADE 审中-公开

    公开(公告)号：US20180080460A1

    公开(公告)日：2018-03-22

    申请号：US15272018

    申请日：2016-09-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： John David Stampfli ,  John David Dyer

    IPC: F04D29/38 ,  F04D29/54 ,  F04D29/32 ,  F02C3/04

    CPC classification number: F04D29/324 ,  F01D5/141 ,  F05D2220/3218 ,  F05D2250/74 ,  Y02T50/673

    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

    COMPRESSOR END-WALL TREATMENT WITH MULTIPLE FLOW AXES
    9.
    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。

    Airfoil shape for thirteenth stage compressor rotor blade
    10.
    发明授权
    Airfoil shape for thirteenth stage compressor rotor blade 有权

    公开(公告)号：US10415464B2

    公开(公告)日：2019-09-17

    申请号：US15272008

    申请日：2016-09-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： John David Stampfli ,  John David Dyer

    IPC: F02C3/04 ,  F04D29/32 ,  F04D29/54 ,  F01D5/14

    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

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