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    Clearance control system for a rotary machine and method of controlling a clearance
    12.
    发明授权
    Clearance control system for a rotary machine and method of controlling a clearance 有权
    用于旋转机器的间隙控制系统和控制间隙的方法

    公开(公告)号：US09488063B2

    公开(公告)日：2016-11-08

    申请号：US14025179

    申请日：2013-09-12

    Applicant: General Electric Company

    Inventor： David Martin Johnson ,  Radu Ioan Danescu

    IPC: F01D11/18 ,  F01D11/22 ,  F01D11/24

    CPC classification number: F01D11/24 ,  F01D11/18 ,  F01D11/22 ,  Y02T50/671

    Abstract: A clearance control system for a rotary machine includes an outer casing including an outer casing main portion having a first radial thickness, wherein the outer casing is configured to expand at a first time rate of thermal expansion. Also included is an inner casing disposed between the outer casing and a rotary portion, the inner casing including an inner casing main portion having a second radial thickness that is less than the first radial thickness, wherein the inner casing is configured to expand at a second time rate of thermal expansion that is greater than the first time rate of thermal expansion of the outer casing. Further included is an inner casing leg configured to separate from an outer casing leg during expansion of the inner casing and configured to engage the outer casing leg during contraction of the inner casing.

    Abstract translation: 一种用于旋转机器的间隙控制系统包括：外壳，包括具有第一径向厚度的外壳主体部分，其中外壳构造成以第一时间热膨胀率膨胀。 还包括设置在外壳和旋转部分之间的内壳，内壳包括具有小于第一径向厚度的第二径向厚度的内壳主体部分，其中内壳构造成在第二径向下扩张 时间热膨胀率大于外壳的第一次热膨胀率。 还包括内壳腿，其构造成在内壳膨胀期间与外壳腿分离，并且构造成在内壳收缩期间与外壳腿接合。

    Inducer Guide Vanes
    14.
    发明申请
    Inducer Guide Vanes 有权
    诱导指南

    公开(公告)号：US20140140805A1

    公开(公告)日：2014-05-22

    申请号：US13669046

    申请日：2012-11-05

    Applicant: General Electric Company

    Inventor： Richard William Johnson ,  David Martin Johnson ,  Bradley James Miller ,  Mitchell Merrill

    IPC: F02C6/08

    CPC classification number: F02C6/08 ,  F01D25/14 ,  F04D29/545 ,  F04D29/701

    Abstract: According to one embodiment, there is disclosed an inducer assembly for use with a gas turbine engine. The inducer assembly may include a cavity. The inducer assembly may also include an inducer in fluid communication with the cavity. Moreover, the inducer assembly may include at least one guide vane disposed within the cavity.

    Abstract translation: 根据一个实施例，公开了一种用于燃气涡轮发动机的诱导器组件。 诱导器组件可以包括空腔。 诱导器组件还可以包括与空腔流体连通的诱导器。 此外，导流器组件可以包括设置在空腔内的至少一个引导叶片。

    GAS TURBINE CASING THERMAL CONTROL DEVICE
    15.
    发明申请
    GAS TURBINE CASING THERMAL CONTROL DEVICE 有权
    气体涡轮机箱体热控制装置

    公开(公告)号：US20140112759A1

    公开(公告)日：2014-04-24

    申请号：US13654672

    申请日：2012-10-18

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Matthew Stephen Casavant ,  Kenneth Damon Black ,  David Martin Johnson ,  Radu Ioan Danescu

    IPC: F02C7/12

    CPC classification number: F01D11/24 ,  F01D11/025 ,  F01D11/14 ,  F01D11/16 ,  F01D11/18 ,  F01D11/20

    Abstract: A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed.

    Abstract translation: 用于将气体冲击引导到燃气涡轮机的内壳体的装置可以包括被配置为附接到内壳体的外表面的板。 当板被附接到内壳的区域和与第一表面相对的第二表面时，板具有与内壳相对的第一表面。 板从第一表面到第二表面限定穿过板的多个孔。 这些孔以对应于期望的优先冲击图案的板中的预定不均匀分布布置，用于在燃气轮机的操作期间从区域提供不均匀的热传递，以便控制内壳跨过该区域的温度。 可以进行各种选择和修改。 还公开了相关的燃气轮机组件。

    HELICAL SEAL SYSTEM FOR A TURBOMACHINE
    17.
    发明申请
    HELICAL SEAL SYSTEM FOR A TURBOMACHINE 有权
    涡轮机的密封系统

    公开(公告)号：US20150040566A1

    公开(公告)日：2015-02-12

    申请号：US13960285

    申请日：2013-08-06

    Applicant: General Electric Company

    Inventor： Radu Ioan Danescu ,  David Martin Johnson

    IPC: F01D11/02

    CPC classification number: F01D11/02 ,  F01D11/001 ,  F05D2250/25 ,  F05D2250/281

    Abstract: A helical seal system includes a first component, and a second component rotatable relative to the first component. The second component extends from a high pressure portion to a low pressure portion through an intermediate portion. A helical seal is provided on the intermediate portion of the second component. The helical seal includes at least one thread component having a pitch that is configured and disposed to draw fluids from the low pressure portion toward the high pressure portion when the second component is rotated.

    Abstract translation: 螺旋密封系统包括第一部件和相对于第一部件可旋转的第二部件。 第二部件通过中间部分从高压部分延伸到低压部分。 螺旋形密封件设置在第二部件的中间部分上。 所述螺旋形密封件包括至少一个螺纹部件，所述螺纹部件具有螺距，该螺距构造和设置成当第二部件旋转时将流体从低压部分抽向高压部分。

    SYSTEM AND METHOD RELATING TO AXIAL POSITIONING TURBINE CASINGS AND BLADE TIP CLEARANCE IN GAS TURBINE ENGINES
    18.
    发明申请
    SYSTEM AND METHOD RELATING TO AXIAL POSITIONING TURBINE CASINGS AND BLADE TIP CLEARANCE IN GAS TURBINE ENGINES 有权
    与涡轮发动机轴向定位涡轮机和叶片间隙相关的系统和方法

    公开(公告)号：US20150037133A1

    公开(公告)日：2015-02-05

    申请号：US13955721

    申请日：2013-07-31

    Applicant: General Electric Company

    Inventor： Matthew Stephen Casavant ,  David Martin Johnson

    IPC: F01D11/16

    CPC classification number: F01D11/16 ,  F01D11/18 ,  F01D25/246 ,  F05D2250/232

    Abstract: A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means.

    Abstract translation: 一种用于在瞬时发动机运转期间根据流路中的变化的压力被动地改变燃气轮机的内壳的轴向位置的系统。 该系统可以包括：连接组件，其可滑动地将内壳体连接到外壳体，用于内壳体在第一位置和第二位置之间的轴向运动; 用于相对于流路压力加压环空的装置; 用于将内壳轴向预加载到第一位置的偏压装置; 以及内壳体接收表面，其构造成在所述环形空间中承受压力，用于与所述偏压装置的轴向预载荷相对轴向地加载所述内壳体。

    FLOW SLEEVE FOR THERMAL CONTROL OF A DOUBLE-WALL TURBINE SHELL AND RELATED METHOD
    19.
    发明申请
    FLOW SLEEVE FOR THERMAL CONTROL OF A DOUBLE-WALL TURBINE SHELL AND RELATED METHOD 有权
    用于双壁涡轮壳体的热控制的流动管道及相关方法

    公开(公告)号：US20140341702A1

    公开(公告)日：2014-11-20

    申请号：US13794136

    申请日：2013-03-11

    Applicant: General Electric Company

    Inventor： Radu Ioan DENESCU ,  David Martin Johnson ,  Kenneth Damon Black ,  Christopher Paul Cox ,  Ozgur Bozkurt

    IPC: F01D19/02 ,  F01D25/08

    CPC classification number: F01D25/08 ,  F01D11/24 ,  F01D19/02 ,  F01D25/26 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2260/20

    Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.

    Abstract translation: 涡轮壳体包括适于将一个或多个涡轮级包围在燃气涡轮发动机中的至少一个壳体; 至少一个壳体中的空气入口; 固定到所述至少一个壳体的内表面的流动套筒，所述流动套筒包括至少两个弧形段。 每个弧形段包括一个弧形基座，一对侧壁，从基座的径向向外延伸，从而形成由基部，侧壁和内表面限定的周向延伸的流动通道。 空气入口与流动通道对准，并且套筒构造成将在通道中流动的空气沿周向，径向和轴向方向（包括沿着至少一个壳体的内表面）分布在一个或多个涡轮机台附近的空间中。

    GAS TURBINE THERMAL CONTROL AND RELATED METHOD
    20.
    发明申请
    GAS TURBINE THERMAL CONTROL AND RELATED METHOD 有权
    燃气轮机热控制及相关方法

    公开(公告)号：US20140109590A1

    公开(公告)日：2014-04-24

    申请号：US13654689

    申请日：2012-10-18

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Matthew Stephen Casavant ,  Kenneth Damon Black ,  David Martin Johnson ,  Radu Ioan Danescu

    IPC: F02C7/18

    CPC classification number: F01D11/24 ,  F01D11/025 ,  F01D11/14 ,  F01D11/16 ,  F01D11/18 ,  F01D11/20 ,  F01D25/14 ,  F01D25/26 ,  F02C7/12

    Abstract: Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.

    Abstract translation: 通过从压缩机供给热控制气体到外壳和内壳之间的空间，为燃气轮机壳体提供热控制，并且通过多个孔将热控制气体从空间传递通过内壳体中的开口 通过附接到内壳的外表面的板限定。 孔以预定的不均匀分布布置，其对应于期望的优先冲击图案以提供不均匀的热传递。 燃气轮机热控制组件包括在燃气轮机运行期间通过从内壳的径向外侧到燃气轮机内部的热控制气体流动路径，从内壳提供优先传热的结构。

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