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    Turbine bucket having non-axisymmetric endwall contour and profile
    1.
    发明授权
    Turbine bucket having non-axisymmetric endwall contour and profile 有权

    公开(公告)号：US10190417B2

    公开(公告)日：2019-01-29

    申请号：US15019461

    申请日：2016-02-09

    Applicant: General Electric Company

    Inventor： Lee Larned Brozyna ,  Mehmet Suleyman Ciray ,  Mark Andrew Jones

    IPC: F01D5/14

    Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.

    TURBOMACHINE ROTOR BLADE
    2.
    发明申请
    TURBOMACHINE ROTOR BLADE 审中-公开

    公开(公告)号：US20180355729A1

    公开(公告)日：2018-12-13

    申请号：US15615876

    申请日：2017-06-07

    Applicant: General Electric Company

    Inventor： Mark Andrew Jones ,  Bradley Taylor Boyer

    IPC: F01D5/18 ,  F01D5/20

    CPC classification number: F01D5/187 ,  F01D5/20 ,  F01D5/225 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2250/314 ,  F05D2250/52 ,  F05D2260/201

    Abstract: A rotor blade includes an airfoil defining at least one cooling passage and a camber line extending from a leading edge to a trailing edge. The rotor blade further includes a tip shroud coupled to the airfoil, the tip shroud and the airfoil defining a core fluidly coupled to the at least one cooling passage, the core including a plurality of outlet apertures, each of the plurality of outlet apertures including an opening defined in an exterior surface of the tip shroud. A first outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is between 15 degrees from parallel to and parallel to the camber line at the trailing edge. A second outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is greater than 15 degrees from parallel to the camber line at the trailing edge.

    SNUBBER CONFIGURATIONS FOR TURBINE ROTOR BLADES
    4.
    发明申请
    SNUBBER CONFIGURATIONS FOR TURBINE ROTOR BLADES 审中-公开
    用于涡轮转子叶片的SNUBBER配置

    公开(公告)号：US20150176413A1

    公开(公告)日：2015-06-25

    申请号：US14136403

    申请日：2013-12-20

    Applicant: General Electric Company

    Inventor： Joseph Anthony Weber ,  Mark Andrew Jones

    IPC: F01D5/22

    CPC classification number: F01D5/225 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A rotor blade for use in a turbine of a combustion turbine engine. The rotor blade may include an airfoil having a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between the root and an outboard tip. The rotor blade may further include dual snubber shrouds positioned on the airfoil. Each of the dual snubber shrouds may be configured to engage a corresponding snubber shroud on at least one neighboring rotor blade upon installation.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮机的转子叶片。 转子叶片可以包括具有凹压力侧壁和在相应的前缘和后缘之间轴向延伸并且在根部和外侧梢之间径向延伸的凸形吸力侧壁的翼型件。 转子叶片还可以包括位于翼型上的双缓冲罩。 每个双缓冲器护罩可构造成在安装时在至少一个相邻的转子叶片上接合相应的缓冲罩。

    TIP SHROUDS OF TURBINE ROTOR BLADES AND METHODS OF MANUFACTURE RELATED THERETO
    5.
    发明申请
    TIP SHROUDS OF TURBINE ROTOR BLADES AND METHODS OF MANUFACTURE RELATED THERETO 审中-公开
    涡轮转子叶片的尖头和制造方法

    公开(公告)号：US20140255194A1

    公开(公告)日：2014-09-11

    申请号：US13725649

    申请日：2012-12-21

    Applicant: General Electric Company

    Inventor： Mark Andrew Jones

    IPC: F01D5/22

    CPC classification number: F01D5/225 ,  B23P15/04 ,  F01D5/005 ,  F01D5/147 ,  Y02T50/673 ,  Y10T29/49336

    Abstract: A rotor blade for use in a turbine of a turbine engine is described. The rotor blade may include an airfoil that extends from a connection with a root. The airfoil may include a pressure sidewall and a suction sidewall that define an outer periphery and an outboard tip. The rotor blade may further include a tip shroud assembly disposed at the outboard tip of the airfoil. The tip shroud assembly includes a non-integral tip shroud.

    Abstract translation: 描述了用于涡轮发动机的涡轮机的转子叶片。 转子叶片可以包括从与根部的连接部延伸的翼型件。 翼型件可以包括限定外周和外侧末端的压力侧壁和抽吸侧壁。 转子叶片还可以包括设置在翼型的外侧端部处的尖端护罩组件。 尖端护罩组件包括非整体式尖端护罩。

    Turbomachine Blade Cooling Cavity
    6.
    发明申请
    Turbomachine Blade Cooling Cavity 审中-公开

    公开(公告)号：US20180216474A1

    公开(公告)日：2018-08-02

    申请号：US15421519

    申请日：2017-02-01

    Applicant: General Electric Company

    Inventor： Mark Andrew Jones

    IPC: F01D5/18 ,  F01D5/14

    CPC classification number: F01D5/187 ,  F01D5/225 ,  F05D2240/81 ,  F05D2260/22141

    Abstract: The present disclosure is directed to a blade for a turbomachine. The blade includes an airfoil having a pressure side surface and a suction side surface extending from a leading edge to a trailing edge. The airfoil defines a camber line positioned between the pressure side surface and the suction side surface and extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and defines a cooling cavity therein. The cooling cavity includes one or more turbulators positioned in one or two regions of a forward region, a central region, and an aft region.

    Turbine rotor blade for a turbine section of a gas turbine
    7.
    发明授权
    Turbine rotor blade for a turbine section of a gas turbine 有权

    公开(公告)号：US09810070B2

    公开(公告)日：2017-11-07

    申请号：US13894622

    申请日：2013-05-15

    Applicant: General Electric Company

    Inventor： David Richard Johns ,  Mark Andrew Jones

    IPC: F01D5/08 ,  F01D5/18 ,  F01D5/30

    CPC classification number: F01D5/084 ,  F01D5/081 ,  F01D5/187 ,  F01D5/3007 ,  F05D2240/81 ,  F05D2260/201

    Abstract: A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls.

    Turbomachine rotor blade
    9.
    发明授权
    Turbomachine rotor blade 有权

    公开(公告)号：US10577945B2

    公开(公告)日：2020-03-03

    申请号：US15638603

    申请日：2017-06-30

    Applicant: General Electric Company

    Inventor： Robert Alan Brittingham ,  Mark Andrew Jones

    IPC: F01D5/18 ,  F01D5/14 ,  F01D5/20 ,  F01D5/22

    Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a trailing edge surface and defining a cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud includes a radially inner surface. The tip shroud defines a cooling core fluidly coupled to the cooling passage. The cooling core includes at least one of a first outlet aperture having a first opening defined by the radially inner surface or a second outlet aperture having a second opening defined by the trailing edge surface of the airfoil. The first or second outlet apertures eject coolant from the cooling core in a direction of a local flow of combustion gases external to the tip shroud.

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