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    END WALL CONTOUR FOR AN AXIAL FLOW TURBINE STAGE
    1.
    发明申请
    END WALL CONTOUR FOR AN AXIAL FLOW TURBINE STAGE 审中-公开

    公开(公告)号：US20170218769A1

    公开(公告)日：2017-08-03

    申请号：US15010145

    申请日：2016-01-29

    Applicant: General Electric Company

    Inventor： Prem Venugopal ,  Alexander Stein ,  Shourya Prakash Otta ,  Ambady Suresh

    IPC: F01D5/08 ,  F01D5/22

    CPC classification number: F01D5/145 ,  F01D5/143 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/81 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

    Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a contoured flow surface including a purge valley, an elevated bulge and a bowl. The purge valley has a maximum depth at an elevation equal to or greater than a nominal axisymmetric platform surface of the corresponding platform. The purge valley extending tangentially against a purge cavity wall and into the blend area and extending axially from proximate the leading edge of a first airfoil toward the suction side of the first airfoil, and toward the leading edge of a second adjacent airfoil to channel a purge flow. The elevated bulge adjoins the pressure side aft of the leading edge and the bowl adjoins the suction side aft of the leading edge.

    GAS LIFT VALVE ASSEMBLIES HAVING FLUID FLOW BARRIER AND METHODS OF ASSEMBLING SAME
    5.
    发明申请
    GAS LIFT VALVE ASSEMBLIES HAVING FLUID FLOW BARRIER AND METHODS OF ASSEMBLING SAME 有权
    具有流体流动障碍物的气体提升阀组件及其组装方法

    公开(公告)号：US20160145982A1

    公开(公告)日：2016-05-26

    申请号：US14555260

    申请日：2014-11-26

    Applicant: General Electric Company

    Inventor： Shourya Prakash Otta ,  Norman Arnold Turnquist ,  Roderick Mark Lusted ,  Xuele Qi

    IPC: E21B43/12 ,  F16K27/00 ,  E21B34/06

    CPC classification number: E21B43/123 ,  E21B34/06 ,  F16K1/42 ,  F16K1/443 ,  F16K15/025 ,  F16K15/063 ,  F16K25/00

    Abstract: A gas lift valve assembly includes a housing, a check valve, and a fluid flow barrier. The housing defines an inlet port, an outlet port, and a main flow passage providing fluid communication between the inlet port and the outlet port. The main flow passage has an upstream end and a downstream end. The check valve includes a sealing element disposed at the downstream end of the main flow passage, and a valve member configured to sealingly engage the sealing element. The valve member is movable between an open position in which fluid flow is permitted in a downstream direction, and a closed position in which the valve member inhibits fluid flow in an upstream direction. The fluid flow barrier is disposed within the main flow passage, and is configured to direct fluid flow away from the sealing element when the valve member is in the open position.

    Abstract translation: 气举阀组件包括壳体，止回阀和流体流动阻挡件。 壳体限定入口端口，出口端口和主流路，其提供入口和出口之间的流体连通。 主流路具有上游端和下游端。 止回阀包括设置在主流路的下游端的密封元件和构造成密封地接合密封元件的阀构件。 阀构件可在下游方向允许流体流动的打开位置和阀构件阻止流体沿上游方向流动的关闭位置之间移动。 流体阻流板设置在主流路内，并且构造成当阀构件处于打开位置时将流体流动从密封元件引导。

    AIRCRAFT ENGINE STRUT ASSEMBLY AND METHODS OF ASSEMBLING THE SAME
    6.
    发明申请
    AIRCRAFT ENGINE STRUT ASSEMBLY AND METHODS OF ASSEMBLING THE SAME 审中-公开
    飞机发动机组件及其组装方法

    公开(公告)号：US20150114006A1

    公开(公告)日：2015-04-30

    申请号：US14065840

    申请日：2013-10-29

    Applicant: General Electric Company

    Inventor： Chiong Siew Tan ,  Byron Andrew Pritchard ,  Shourya Prakash Otta

    IPC: F02C7/20

    CPC classification number: F02C7/20 ,  F01D5/146 ,  F01D17/08 ,  F01D21/003 ,  F01D25/162 ,  F05D2240/126 ,  F05D2250/71 ,  F05D2260/607 ,  F05D2270/20 ,  F05D2270/3061 ,  F05D2270/312 ,  F05D2270/313 ,  F05D2270/80 ,  Y02T50/673 ,  Y02T50/675 ,  Y10T29/49229

    Abstract: An engine strut for providing fan hub frame structural support and monitoring an air flow within an aircraft engine includes an airfoil coupled to the aircraft engine and has a first portion and a second portion. The first portion is positioned upstream of the second portion with respect to the air flow. A shield is coupled to the engine and positioned between the first portion and the second portion. The shield includes a first side spaced from the first portion and defining a first flow path with the first portion. The shield further includes a second side spaced from the second portion and defining a second flow path with the second portion. At least one sensor is coupled to the aircraft engine and positioned in flow communication with the second flow path.

    Abstract translation: 用于提供风扇轮毂框架结构支撑和监测飞行器发动机内的空气流的发动机支柱包括联接到飞行器发动机并具有第一部分和第二部分的翼型件。 第一部分相对于空气流定位在第二部分的上游。 屏蔽件联接到发动机并且定位在第一部分和第二部分之间。 屏蔽包括与第一部分间隔开并且限定具有第一部分的第一流动路径的第一侧。 屏蔽还包括与第二部分间隔开并与第二部分限定第二流路的第二侧。 至少一个传感器耦合到飞行器引擎并且与第二流动路径流动连通地定位。

    Inlet assembly for an aircraft aft fan
    7.
    发明授权
    Inlet assembly for an aircraft aft fan 有权

    公开(公告)号：US10704418B2

    公开(公告)日：2020-07-07

    申请号：US16377736

    申请日：2019-04-08

    Applicant: General Electric Company

    Inventor： Kishore Ramakrishnan ,  Shourya Prakash Otta

    IPC: B64D33/02 ,  F01D25/24 ,  B64D29/00 ,  B64D27/12 ,  B64C30/00

    Abstract: An engine for mounting in or to an aircraft includes a stage of compression airfoils rotatable about a central axis; a casing surrounding the stage of compression airfoils and defining an inlet; and a low-distortion inlet assembly mounted within the inlet. The inlet assembly includes one or more structural members mounted at predetermined locations around a circumference of the central axis within the inlet, the predetermined locations defining an airflow distortion exceeding a predetermined threshold; and at least one airflow modifying element configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils.

    End wall contour for an axial flow turbine stage
    9.
    发明授权
    End wall contour for an axial flow turbine stage 有权

    公开(公告)号：US10240462B2

    公开(公告)日：2019-03-26

    申请号：US15010145

    申请日：2016-01-29

    Applicant: General Electric Company

    Inventor： Prem Venugopal ,  Alexander Stein ,  Shourya Prakash Otta ,  Ambady Suresh

    IPC: F01D5/14

    Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a contoured flow surface including a purge valley, an elevated bulge and a bowl. The purge valley has a maximum depth at an elevation equal to or greater than a nominal axisymmetric platform surface of the corresponding platform. The purge valley extending tangentially against a purge cavity wall and into the blend area and extending axially from proximate the leading edge of a first airfoil toward the suction side of the first airfoil, and toward the leading edge of a second adjacent airfoil to channel a purge flow. The elevated bulge adjoins the pressure side aft of the leading edge and the bowl adjoins the suction side aft of the leading edge.

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