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    Shroud configurations for turbine rotor blades
    1.
    发明授权
    Shroud configurations for turbine rotor blades 有权

    公开(公告)号：US10648346B2

    公开(公告)日：2020-05-12

    申请号：US15203027

    申请日：2016-07-06

    Applicant: General Electric Company

    Inventor： Xiuzhang James Zhang ,  Kevin Richard Kirtley ,  Lisa DeBellis

    IPC: F01D5/20 ,  F01D5/22 ,  F01D11/08

    Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.

    Turbomachine Blade Cooling Structure and Related Methods
    2.
    发明申请
    Turbomachine Blade Cooling Structure and Related Methods 审中-公开

    公开(公告)号：US20180355727A1

    公开(公告)日：2018-12-13

    申请号：US15620896

    申请日：2017-06-13

    Applicant: General Electric Company

    Inventor： Jalindar Appa Walunj ,  Shashwat Swami Jaiswal ,  Stephen Paul Wassynger ,  Xiuzhang James Zhang

    IPC: F01D5/08 ,  F01D5/22

    Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.

    Sealing arrangement for a turbine system and method of sealing between two turbine components
    3.
    发明授权
    Sealing arrangement for a turbine system and method of sealing between two turbine components 有权
    涡轮机系统的密封装置和两个涡轮机部件之间的密封方法

    公开(公告)号：US09464536B2

    公开(公告)日：2016-10-11

    申请号：US13654822

    申请日：2012-10-18

    Applicant: General Electric Company

    Inventor： Xiuzhang James Zhang ,  Gary Michael Itzel ,  Ibrahim Sezer

    IPC: F01D11/12 ,  F01D11/00

    CPC classification number: F01D11/006 ,  F01D11/122

    Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.

    Abstract translation: 涡轮机系统的密封装置包括具有外部尖端的桶，以及从外部末端径向向外延伸的至少一个铲斗脊，所述至少一个铲斗脊包含可磨损材料。 还包括从桶的外端径向向外设置的固定护罩。 还包括至少一个护罩脊，其从固定护罩朝向桶的外部末端径向向内延伸，所述至少一个护罩脊包括可磨损材料。

    Turbine airfoil turbulator arrangement
    5.
    发明授权
    Turbine airfoil turbulator arrangement 有权

    公开(公告)号：US09995146B2

    公开(公告)日：2018-06-12

    申请号：US14699607

    申请日：2015-04-29

    Applicant: General Electric Company

    Inventor： Adebukola Oluwaseun Benson ,  Nicholas Alvin Hogberg ,  Gary Michael Itzel ,  Mitchell Allan Merrill ,  Xiuzhang James Zhang

    IPC: F01D5/18

    CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141

    Abstract: A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

    ROTOR BLADE HAVING A FLARED TIP
    8.
    发明申请
    ROTOR BLADE HAVING A FLARED TIP 审中-公开
    带有刀尖的转子叶片

    公开(公告)号：US20160319673A1

    公开(公告)日：2016-11-03

    申请号：US14699321

    申请日：2015-04-29

    Applicant: General Electric Company

    Inventor： Jeffrey Clarence Jones ,  Xiuzhang James Zhang ,  Mitchell Allan Merrill

    IPC: F01D5/18 ,  F02C7/18 ,  F02C3/04

    CPC classification number: F01D5/187 ,  F01D5/20 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2240/35 ,  F05D2250/294 ,  F05D2250/324 ,  F05D2260/202

    Abstract: A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.

    Abstract translation: 转子叶片包括具有形成在叶片尖端处的叶片尖端和尖端腔的翼型件。 尖端腔包括从尖端径向向内凹入并且被翼型的压力和吸力侧壁连续围绕的顶盖。 尖端帽还包括一个孔，其延伸穿过顶端帽，并提供在翼型内限定的内腔与尖端腔之间的流体连通。 排气口提供通过压力侧壁，吸力侧壁或后缘中的一个流体连通出口腔。 限定尖端腔的吸入侧壁和压力侧壁中的至少一个的一部分相对于径向方向从尖端腔倾斜向外延伸。

    ROTOR BLADE HAVING A FLARED TIP
    9.
    发明申请
    ROTOR BLADE HAVING A FLARED TIP 审中-公开
    带有刀尖的转子叶片

    公开(公告)号：US20160319672A1

    公开(公告)日：2016-11-03

    申请号：US14699308

    申请日：2015-04-29

    Applicant: General Electric Company

    Inventor： Jeffrey Clarence Jones ,  Xiuzhang James Zhang

    IPC: F01D5/18

    CPC classification number: F01D5/20 ,  F05D2250/314 ,  F05D2250/324 ,  F05D2250/713

    Abstract: A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The blade tip defines a radially outer surface of the airfoil. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded by pressure and suction side walls of the airfoil. The tip cap is in fluid communication with an internal cavity defined within the airfoil. A portion of at least one of the suction side wall or the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity. A plurality of slots is defined in at least one of the suction side wall or the pressure side wall along the radially outer surface proximate to the trailing edge of the airfoil.

    Abstract translation: 转子叶片包括具有形成在叶片尖端处的叶片尖端和尖端腔的翼型件。 叶片尖端限定翼型件的径向外表面。 尖端腔包括从尖端径向向内凹入并被翼型的压力和吸力侧壁包围的顶盖。 顶盖与限定在翼型内的内部空腔流体连通。 限定尖端腔的吸入侧壁或压力侧壁中的至少一个的一部分从尖端腔倾斜向外延伸。 吸入侧壁或压力侧壁中的至少一个沿着靠近翼型的后缘的径向外表面限定多个狭槽。

    Rotor blade and method for cooling the rotor blade
    10.
    发明授权
    Rotor blade and method for cooling the rotor blade 有权
    转子叶片和冷却转子叶片的方法

    公开(公告)号：US09334742B2

    公开(公告)日：2016-05-10

    申请号：US13645585

    申请日：2012-10-05

    Applicant: General Electric Company

    Inventor： Xiuzhang James Zhang ,  Adebukola Benson ,  Zhirui Dong

    IPC: F01D5/00 ,  F01D5/20

    CPC classification number: F01D5/20

    Abstract: A rotor blade includes an airfoil having a tip plate that extends across an outer radial end. A rim extends radially outward from the tip plate and surrounds at least a portion of the airfoil and includes a concave portion opposed to a convex portion. A plurality of dividers extend between the concave and convex portions to define a plurality of pockets between the concave and convex portions at the outer radial end. A plurality of cooling passages through the tip plate provide fluid communication through the tip plate to the plurality of pockets. A first fluid passage in at least one divider provides fluid communication between adjacent pockets across the at least one divider.

    Abstract translation: 转子叶片包括具有延伸穿过外径向端的顶板的翼型件。 边缘从顶板径向向外延伸并且包围翼型的至少一部分并且包括与凸部相对的凹部。 多个分隔件在凹部和凸部之间延伸以在外径向端部处在凹部和凸部之间限定多个凹穴。 通过顶板的多个冷却通道提供通过顶板到多个凹穴的流体连通。 至少一个分隔器中的第一流体通道提供穿过至少一个分隔器的相邻袋之间的流体连通。

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