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    Spacers and turbines
    1.
    发明授权
    Spacers and turbines 有权
    隔板和涡轮机

    公开(公告)号：US08070448B2

    公开(公告)日：2011-12-06

    申请号：US12261305

    申请日：2008-10-30

    申请人： Mark C. Morris ,  Milton Ortiz ,  David Waldman ,  James Kroeger

    发明人： Mark C. Morris ,  Milton Ortiz ,  David Waldman ,  James Kroeger

    IPC分类号： F04D29/34

    CPC分类号： F01D11/008 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676

    摘要： Spacers and turbines are provided. In an embodiment, and by way of example only, a spacer includes a strip, a first retention flange, and a second retention flange. The strip has a first edge, a second edge, and an impingement surface, and the impingement surface extends axially along the strip between the first edge and the second edge and is substantially flat. The first retention flange is recessed relative to the impingement surface and extends away from the first edge of the strip. The second retention flange is recessed relative to the impingement surface and extends away from the second edge of the strip.

    摘要翻译： 提供隔板和涡轮机。 在一个实施例中，仅作为示例，间隔件包括条带，第一保持凸缘和第二保持凸缘。 带材具有第一边缘，第二边缘和冲击表面，并且冲击表面沿第一边缘和第二边缘之间的条带轴向延伸并且基本上是平坦的。 第一保持凸缘相对于冲击表面凹陷并且远离带的第一边缘延伸。 第二保持凸缘相对于冲击表面凹陷并且远离带的第二边缘延伸。

    SPACERS AND TURBINES
    2.
    发明申请
    SPACERS AND TURBINES 有权
    间隔和涡轮

    公开(公告)号：US20100111699A1

    公开(公告)日：2010-05-06

    申请号：US12261305

    申请日：2008-10-30

    申请人： Mark C. Morris ,  Milton Ortiz ,  David Waldman ,  James Kroeger

    发明人： Mark C. Morris ,  Milton Ortiz ,  David Waldman ,  James Kroeger

    IPC分类号： F01D5/30

    CPC分类号： F01D11/008 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676

    摘要： Spacers and turbines are provided. In an embodiment, and by way of example only, a spacer includes a strip, a first retention flange, and a second retention flange. The strip has a first edge, a second edge, and an impingement surface, and the impingement surface extends axially along the strip between the first edge and the second edge and is substantially flat. The first retention flange is recessed relative to the impingement surface and extends away from the first edge of the strip. The second retention flange is recessed relative to the impingement surface and extends away from the second edge of the strip

    摘要翻译： 提供隔板和涡轮机。 在一个实施例中，仅作为示例，间隔件包括条带，第一保持凸缘和第二保持凸缘。 带材具有第一边缘，第二边缘和冲击表面，并且冲击表面沿第一边缘和第二边缘之间的条带轴向延伸并且基本上是平坦的。 第一保持凸缘相对于冲击表面凹陷并且远离带的第一边缘延伸。 第二保持凸缘相对于冲击表面凹陷并且远离带的第二边缘延伸

    High effectiveness cooled turbine vane or blade
    3.
    发明授权
    High effectiveness cooled turbine vane or blade 有权
    高效冷却涡轮叶片或叶片

    公开(公告)号：US06974308B2

    公开(公告)日：2005-12-13

    申请号：US09992250

    申请日：2001-11-14

    申请人： Steve H. Halfmann ,  Yong W. Kim ,  Mark C. Morris ,  Milton Ortiz ,  David R. Pack ,  Craig A. Wilson

    发明人： Steve H. Halfmann ,  Yong W. Kim ,  Mark C. Morris ,  Milton Ortiz ,  David R. Pack ,  Craig A. Wilson

    IPC分类号： F01D5/18 ,  F01D5/16 ,  F01D9/06

    CPC分类号： B22C9/04 ,  B22C9/103 ,  F01D5/187 ,  F05D2230/21 ,  F05D2260/202 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

    摘要： A robust multiple-walled, multi-pass, high cooling effectiveness cooled turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded turbine rotors. The vane or blade design allows the turbine inlet temperature to increase over current technology levels while simultaneously reducing turbine cooling to low levels. A multi-wall cooling system is described, which meets the inherent conflict to maximize the flow area of the cooling passages while retaining the required section thickness to meet the structural requirements. Independent cooling circuits for the vane or blade's pressure and suction surfaces allow the cooling of the airfoil surfaces to be tailored to specific heat load distributions (that is, the pressure surface circuit is an independent forward flowing serpentine while the suction surface is an independent rearward flowing serpentine). The cooling air for the independent circuits is supplied through separate passages at the base of the vane or blade. The cooling air follows intricate passages to feed the serpentine thin outer wall passages, which incorporate pin fins, turbulators, etc. These passages, while satisfying the aero/thermal/stress requirements, are of a manufacturing configuration that may be cast with single crystal materials using conventional casting techniques.

    摘要翻译： 为了便于制造而设计的强大的多层，多通，高冷却效率的冷却涡轮叶片或叶片，使得高负载涡轮转子上的冷却流量最小化。 叶片或叶片设计允许涡轮进口温度升高超过当前技术水平，同时将涡轮机冷却降低到低水平。 描述了一种多壁冷却系统，其满足固有的冲突，以最大化冷却通道的流动面积，同时保持所需的部分厚度以满足结构要求。 用于叶片或叶片的压力和吸力表面的独立冷却回路允许翼型表面的冷却根据特定的热负荷分布进行调整（即，压力表面回路是独立的向前流动的蛇形管，而吸力表面是独立的向后流动 蛇纹石）。 用于独立回路的冷却空气通过在叶片或叶片的基部处的分开的通道供应。 冷却空气跟随复杂的通道，以供入蛇形薄壁外壁通道，这些通道包括销翅片，湍流器等。这些通道在满足航空/热/应力要求的同时，具有可以用单晶材料铸造的制造结构 使用常规铸造技术。

    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。

    IMPELLER BACKFACE SHROUD FOR USE WITH A GAS TURBINE ENGINE
    9.
    发明申请
    IMPELLER BACKFACE SHROUD FOR USE WITH A GAS TURBINE ENGINE 有权
    使用燃气涡轮发动机的叶轮背面SHROUD

    公开(公告)号：US20110299972A1

    公开(公告)日：2011-12-08

    申请号：US12794433

    申请日：2010-06-04

    申请人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

    发明人： Mark C. Morris ,  Alexander MirzaMoghadam ,  Khosro Molla Hosseini ,  Kin Poon ,  Jeff Howe ,  Alan G. Tiltman

    IPC分类号： F01D1/00

    CPC分类号： F01D3/025

    摘要： An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

    摘要翻译： 公开了一种用于燃气涡轮发动机的叶轮或轴向级压缩机盘背面罩。 背面护罩包括但不限于具有表面的大致漏斗形的主体。 基本上漏斗形的主体构造成与叶轮或轴向级压缩机盘基本上同轴地静态地安装到燃气涡轮发动机。 当基本上漏斗形的主体与叶轮或轴向级压缩机盘同轴地安装并且与其轴向间隔开时，叶轮或轴向级压缩机盘的表面和背面形成空腔，该空腔将气流部分引导到涡轮机。 气流部分具有切向速度，并且背面护罩的表面中的凹槽通常横向于切向速度定向，以至少部分地干扰气流部分，从而影响空腔中的静压力。

    TURBINE COMPONENTS FOR ENGINES AND METHODS OF FABRICATING THE SAME
    10.
    发明申请
    TURBINE COMPONENTS FOR ENGINES AND METHODS OF FABRICATING THE SAME 有权
    用于发动机的涡轮机组件及其制造方法

    公开(公告)号：US20110135952A1

    公开(公告)日：2011-06-09

    申请号：US12631285

    申请日：2009-12-04

    申请人： Mark C. Morris ,  Tom Strangman ,  Yiping Hu

    发明人： Mark C. Morris ,  Tom Strangman ,  Yiping Hu

    IPC分类号： B32B15/02 ,  B22F7/02

    CPC分类号： B22F5/009 ,  B22F3/1055 ,  B22F7/08 ,  C30B13/00 ,  C30B29/52 ,  Y02P10/295 ,  Y10T428/12028

    摘要： A method is provided that includes depositing metal powder over a seed crystal having a predetermined primary orientation, scanning an initial pattern into the metal powder to melt or sinter the deposited metal powder, and re-scanning the initial pattern to re-melt the scanned metal powder and form an initial layer having the predetermined primary orientation. The method further includes depositing additional metal powder over the initial layer, scanning an additional pattern into the additional metal powder to melt or sinter at least a portion of the additional metal powder, re-scanning the additional pattern to re-melt a portion of the initial layer and the scanned deposited additional metal powder to form a successive layer having the predetermined primary orientation, and repeating the steps of depositing additional metal powder, scanning the additional pattern, and re-scanning the additional pattern, until a final shape of the component is achieved.

    摘要翻译： 提供了一种方法，其包括将金属粉末沉积在具有预定主要取向的晶种上，将初始图案扫描到金属粉末中以熔化或烧结沉积的金属粉末，并重新扫描初始图案以重新熔化扫描的金属 并形成具有预定主要取向的初始层。 该方法还包括在初始层上沉积额外的金属粉末，将另外的图案扫描到附加金属粉末中以熔化或烧结至少一部分附加金属粉末，重新扫描附加图案以重新熔化部分 初始层和扫描的沉积的另外的金属粉末以形成具有预定主要取向的连续层，并且重复沉积额外的金属粉末，扫描附加图案和重新扫描附加图案的步骤，直到组件的最终形状 已完成。