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    METHODS FOR FABRICATING HIGH TEMPERATURE CASTABLE ARTICLES AND GAS TURBINE ENGINE COMPONENTS
    6.
    发明申请
    METHODS FOR FABRICATING HIGH TEMPERATURE CASTABLE ARTICLES AND GAS TURBINE ENGINE COMPONENTS 审中-公开
    制造高温可燃物品和燃气轮机发动机部件的方法

    公开(公告)号：US20120228803A1

    公开(公告)日：2012-09-13

    申请号：US13042893

    申请日：2011-03-08

    申请人： Jason Smoke ,  Wil Baker ,  Dennis Wolski

    发明人： Jason Smoke ,  Wil Baker ,  Dennis Wolski

    IPC分类号： B29C33/38 ,  B29C39/26 ,  B29C39/02 ,  B29C35/08 ,  B29C33/72

    CPC分类号： B29C64/124 ,  B29C35/0261 ,  B29C2035/0855

    摘要： Embodiments of a method are provided for fabricating a high temperature castable article, such as a casting mold or a core. In one embodiment, the method includes the steps of providing a suspension containing a plurality of ceramic particles and a photo-curable monomer; photo-curing selected portions of the suspension to produce a green body coated, at least partially, with uncured suspension; and removing the uncured suspension from the green body under process conditions at which the viscosity of the uncured suspension is reduced. The process conditions include exposing the green body to one of the group consisting of: (i) microwave energy sufficient to excite a dipole moment of the uncured suspension and (ii) sonic energy sufficient to induce shear-thinning of the uncured suspension. The green body is then heat treated to produce the high temperature castable article.

    摘要翻译： 提供了一种用于制造诸如铸模或芯的高温可浇铸制品的方法的实施例。 在一个实施方案中，该方法包括提供包含多个陶瓷颗粒和光可固化单体的悬浮液的步骤; 光固化悬浮液的选定部分以产生至少部分地用未固化的悬浮液涂覆的生坯; 并且在未固化的悬浮液的粘度降低的工艺条件下从生坯中除去未固化的悬浮液。 工艺条件包括将生坯暴露于以下组中的一个：（i）足以激发未固化悬浮液的偶极矩的微波能量和（ii）足以引起未固化悬浮液剪切稀化的声能。 然后将生坯体进行热处理以产生高温浇注物品。

    Gas turbine engine assemblies with recirculated hot gas ingestion
    7.
    发明授权
    Gas turbine engine assemblies with recirculated hot gas ingestion 有权
    具有再循环热气体摄入的燃气涡轮发动机组件

    公开(公告)号：US08262342B2

    公开(公告)日：2012-09-11

    申请号：US12171000

    申请日：2008-07-10

    申请人： Mark C. Morris ,  Jeff Howe ,  Greg Heitland ,  Jason Smoke

    发明人： Mark C. Morris ,  Jeff Howe ,  Greg Heitland ,  Jason Smoke

    IPC分类号： F01D5/14

    CPC分类号： F01D11/001 ,  F01D5/143 ,  F01D5/145 ,  F01D11/02 ,  F01D11/04 ,  Y02T50/673

    摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

    摘要翻译： 燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气流动路径的环形管道壁，所述主流热气体流动路径被配置为接收主流热气流。 组件还包括定子组件，该定子组件包括延伸到主流热气流路径中的定子叶片和在定子组件下游的涡轮转子组件，该涡轮转子组件包括涡轮盘和从涡轮盘延伸到主流热气流中的涡轮叶片 路径。 定子组件和涡轮机组件限定涡轮机盘腔，并且涡轮机盘腔包括再循环空腔，其被配置成将从主流热气流路径吸入的气体再循环回主流热气流路径。

    Turbine blade platform
    8.
    发明授权
    Turbine blade platform 有权
    涡轮叶片平台

    公开(公告)号：US08147197B2

    公开(公告)日：2012-04-03

    申请号：US12401037

    申请日：2009-03-10

    申请人： Mark C. Morris ,  Jason Smoke ,  Jeff Howe ,  Bob Mitlin

    发明人： Mark C. Morris ,  Jason Smoke ,  Jeff Howe ,  Bob Mitlin

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F01D5/30 ,  F05B2240/33 ,  F05D2240/81 ,  F05D2250/292 ,  F05D2260/201 ,  Y02T50/676 ,  Y10S416/50

    摘要： A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.

    摘要翻译： 提供涡轮叶片组件。 涡轮机叶片组件包括涡轮机叶片，其包括空腔和支撑涡轮叶片的叶片平台，空腔延伸到叶片平台中。 叶片平台包括邻近涡轮机叶片的上表面和下表面，下表面包括第一肋，空腔延伸到第一肋中，第一肋联接到下表面，当其远离涡轮叶片延伸时逐渐变细，并且包括 第一端口从空腔延伸到上表面。

    Gas turbine engines with abradable turbine seal assemblies
    9.
    发明授权
    Gas turbine engines with abradable turbine seal assemblies 有权
    具有可磨损涡轮机密封组件的燃气涡轮发动机

    公开(公告)号：US09068469B2

    公开(公告)日：2015-06-30

    申请号：US13224035

    申请日：2011-09-01

    申请人： Bradley Reed Tucker ,  Jason Smoke ,  Mark C. Morris

    发明人： Bradley Reed Tucker ,  Jason Smoke ,  Mark C. Morris

    IPC分类号： F01D11/12 ,  F01D11/00

    CPC分类号： F01D11/122 ,  F01D11/006 ,  F05D2230/313 ,  F05D2240/55 ,  F05D2300/123 ,  Y10T29/49297

    摘要： A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.

    摘要翻译： 燃气涡轮发动机的涡轮部分包括壳体，转子组件和密封组件。 转子组件包括转子盘，联接到转子盘的转子平台以及从转子平台延伸到主流热气流动路径中的转子叶片。 定子组件包括具有定子叶片的定子平台，定子叶片从定子平台延伸到主流热气流动路径中。 所述密封组件包括从所述转子平台沿第一方向延伸的第一流动障碍物，从所述定子平台沿第二方向延伸的第二流动障碍物，所述第一流动障碍物轴向地与所述第二流动盘旋重叠，使得所述第二流动盘旋器为内部 在径向方向上的第一流动捣碎器，施加到第一流动捣碎器的硬涂层，以及施加到第二流动捣碎器的可磨损涂层。