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    METHOD AND SYSTEM TO FACILITATE SEALING IN GAS TURBINES
    31.
    发明申请
    METHOD AND SYSTEM TO FACILITATE SEALING IN GAS TURBINES 有权
    在气体涡轮机中密封的方法和系统

    公开(公告)号：US20150098808A1

    公开(公告)日：2015-04-09

    申请号：US14049020

    申请日：2013-10-08

    Applicant: General Electric Company

    Inventor： Victor John Morgan ,  Gregory Thomas Foster ,  Neelesh Nandkumar Sarawate ,  David Wayne Weber

    IPC: F01D11/08

    CPC classification number: F01D11/08 ,  F01D9/041 ,  F01D11/003 ,  F05D2230/60 ,  F05D2260/38 ,  Y10T29/4932

    Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.

    Abstract translation: 提供了一种在燃气轮机内的部件之间进行密封的方法和系统。 限定在第一部件中的第一凹部接收密封构件。 限定在与第一部件相邻的第二部件中的第二凹部也接收密封部件。 第一和第二凹槽位于通过燃气涡轮机限定的热气路径附近，并限定围绕涡轮机轴线的圆周路径。 密封构件包括沿基本上平行于涡轮机轴线的方向延伸的密封面。 密封构件还包括多个密封层，其中至少一个密封层包括用于促进第一密封构件弯曲的至少一个应力释放区域。

    GAS TURBINE SHROUD COOLING
    32.
    发明申请
    GAS TURBINE SHROUD COOLING 审中-公开
    燃气轮机冷却

    公开(公告)号：US20150013345A1

    公开(公告)日：2015-01-15

    申请号：US13939727

    申请日：2013-07-11

    Applicant: General Electric Company

    Inventor： Christopher Donald Porter ,  Gregory Thomas Foster ,  Aaron Ezekiel Smith ,  David Wayne Weber ,  Michelle J. Rogers

    IPC: F01D25/12

    CPC classification number: F01D25/12 ,  F01D11/24 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    Abstract: A shroud segment for a casing of gas turbine includes a body configured for attachment to the casing proximate a localized critical process location within the casing. The body has a leading edge, a trailing edge, and two side edges. The critical process location is located between the leading edge and the trailing edge when the body is attached to the casing. A cooling passage is defined in the body along one of the side edges with one of an inlet or an outlet proximate the critical process location. The cooling passage is configured large enough to cool the one side edge adjacent the cooling passage to a desired level during operation of the gas turbine. The critical process locations may be related to temperatures, pressures or other measurable features of the gas turbine environment when in use.

    Abstract translation: 用于燃气涡轮机壳体的护罩段包括构造成用于附接到壳体内的主体，该主体靠近壳体内的局部临界过程位置。 主体具有前缘，后缘和两个侧边。 当主体连接到壳体时，临界过程位置位于前缘和后缘之间。 冷却通道在主体中沿着一个侧边缘限定，其中一个入口或出口靠近临界过程位置。 冷却通道被构造成足够大以在燃气轮机的操作期间将邻近冷却通道的一侧边缘冷却到期望的水平。 关键过程位置可能与使用中的燃气轮机环境的温度，压力或其他可测量特征有关。

    Turbine bucket having tip shroud fillet, tip shroud cross-drilled apertures and profile
    34.
    发明授权
    Turbine bucket having tip shroud fillet, tip shroud cross-drilled apertures and profile 有权

    公开(公告)号：US10697308B2

    公开(公告)日：2020-06-30

    申请号：US16170523

    申请日：2018-10-25

    Applicant: General Electric Company

    Inventor： Neil Ristau ,  Zachary James Taylor ,  David Wayne Weber

    IPC: F01D5/18 ,  F01D5/22 ,  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; a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and a tip shroud connected with a second end of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil.

    Intermediate central passage spanning outer walls aft of airfoil leading edge passage
    36.
    发明授权
    Intermediate central passage spanning outer walls aft of airfoil leading edge passage 有权

    公开(公告)号：US10605090B2

    公开(公告)日：2020-03-31

    申请号：US15152684

    申请日：2016-05-12

    Applicant: General Electric Company

    Inventor： Brendon James Leary ,  Gregory Thomas Foster ,  Michelle Jessica Iduate ,  David Wayne Weber

    IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F01D9/06

    Abstract: A turbine blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning a leading edge passage from the radially extending chamber. The rib configuration may also include a first center transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning an intermediate passage from the radially extending chamber directly aft of the leading edge passage. The intermediate passage is defined by the pressure side outer wall, the suction side outer wall, the leading edge transverse rib and the first center transverse rib, and thus spans airfoil between its outer walls.

    Cooling circuit for a multi-wall blade
    37.
    发明授权
    Cooling circuit for a multi-wall blade 有权

    公开(公告)号：US10227877B2

    公开(公告)日：2019-03-12

    申请号：US15239985

    申请日：2016-08-18

    Applicant: General Electric Company

    Inventor： David Wayne Weber ,  Lana Maria Osusky

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/02 ,  F01D25/12 ,  F02C3/04

    Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the pressure and suction side cavities; and a second leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the second leading edge cavity located forward of the first leading edge cavity.

    Cooling circuit for a multi-wall blade
    38.
    发明授权
    Cooling circuit for a multi-wall blade 有权

    公开(公告)号：US10119405B2

    公开(公告)日：2018-11-06

    申请号：US14977078

    申请日：2015-12-21

    Applicant: General Electric Company

    Inventor： David Wayne Weber ,  Brendon James Leary ,  Jacob Charles Perry, II ,  Joseph Anthony Weber

    IPC: F02C1/00 ,  F01D5/18 ,  F01D5/14 ,  F02C3/04

    Abstract: A cooling system according to an embodiment includes: a forked passage cooling circuit, the forked passage cooling circuit including a first leg and a second leg; and an air feed cavity for supplying cooling air to the first leg and the second leg of the forked passage cooling circuit; wherein the first leg of the forked passage cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the forked passage cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels in the multi-wall blade.

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