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    TURBINE ABRADABLE LAYER WITH ZIG ZAG GROOVE PATTERN
    81.
    发明申请
    TURBINE ABRADABLE LAYER WITH ZIG ZAG GROOVE PATTERN 有权
    具有ZIG ZAG GROTVE PATTERN的涡轮不可逆层

    公开(公告)号：US20150240653A1

    公开(公告)日：2015-08-27

    申请号：US14189081

    申请日：2014-02-25

    Applicant: Siemens Aktiengesellschaft

    Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Gm Salam Azad

    IPC: F01D11/12

    CPC classification number: F01D11/122 ,  F01D5/02 ,  F01D5/12 ,  F01D11/14 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/30 ,  F05D2230/10 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/282 ,  F05D2250/294 ,  F05D2250/71 ,  Y10T29/49236

    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with zig-zag pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.

    Abstract translation: 用于涡轮发动机的涡轮机和压缩机壳体可磨损部件实施例，具有锯齿形图案可磨损的表面脊和凹槽。 一些实施方案包括明显的前向上游和后向下游复合多取向凹槽和垂直突出的脊平台形图案，以减少，重定向和/或阻挡下游进入凹槽的叶片尖端气流泄漏，而不是从涡轮叶片翼型件到高压侧。 脊或肋实施例具有第一下部和第二上部耐磨区域。 下部区域优化发动机气流特性，同时优化上部区域以通过比下部区域更容易磨损来最小化叶片尖端间隙和磨损。

    MULTI-STAGE TURBOCHARGER SYSTEM
    83.
    发明申请
    MULTI-STAGE TURBOCHARGER SYSTEM 有权
    多级涡轮增压器系统

    公开(公告)号：US20140144134A1

    公开(公告)日：2014-05-29

    申请号：US13686744

    申请日：2012-11-27

    Applicant: CUMMINS TURBO TECHNOLOGIES LIMITED

    Inventor： James A. McEwan ,  Lee J. Robinson

    IPC: F02B37/22

    CPC classification number: F02B37/013 ,  F01D5/02 ,  F01D25/24 ,  F02B33/40 ,  F02B37/183 ,  F02B37/22 ,  F02B37/225 ,  F02D9/06 ,  F02M26/08 ,  F02M26/10 ,  F02M26/23 ,  F05D2220/40 ,  F05D2240/24 ,  Y02T10/144

    Abstract: A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger (1) and a second relatively large low pressure (LP) turbocharger (2). The turbine (6) of the LP turbocharger (2) is connected in series downstream of the turbine (4) of the HP turbocharger (1) in a first exhaust gas passage (11). An exhaust bypass flow passage (12) provides a bypass flow path around the HP turbine (4). A rotary valve (8) is located at a junction of the bypass flow passage (12) and a first exhaust gas flow passage (11). The rotary valve (8) comprises a valve rotor (19) which is rotatable to selectively permit or block flow to the LP turbine (6) from either the first exhaust gas passage (11) or the bypass gas passage (12).

    Abstract translation: 涡轮增压器系统包括第一相对较小的高压（HP）涡轮增压器（1）和第二较大的低压（LP）涡轮增压器（2）。 在第一废气通道（11）中，LP涡轮增压器（2）的涡轮机（6）在HP涡轮增压器（1）的涡轮机（4）的下游串联连接。 排气旁路流动通道（12）提供围绕HP涡轮机（4）的旁路流动路径。 旋转阀（8）位于旁通流路（12）和第一排气流路（11）的接合处。 旋转阀（8）包括阀转子（19），该阀转子可旋转以选择性地允许或阻止从第一排气通道（11）或旁路气体通道（12）流向LP涡轮机（6）。

    Mobile, Modular, Electrically Powered System For Use in Fracturing Underground Formations Using Liquid Petroleum Gas
    84.
    发明申请
    Mobile, Modular, Electrically Powered System For Use in Fracturing Underground Formations Using Liquid Petroleum Gas 有权
    移动，模块化，电动系统用于使用液体石油气压裂地下地层

    公开(公告)号：US20140096974A1

    公开(公告)日：2014-04-10

    申请号：US13804906

    申请日：2013-03-14

    Applicant: Todd Coli ,  Eldon Schelske

    Inventor： Todd Coli ,  Eldon Schelske

    IPC: E21B43/26

    CPC classification number: E21B43/26 ,  B01F3/0853 ,  B01F7/00008 ,  B01F15/00538 ,  B01F15/0201 ,  B01F2215/0081 ,  F01D15/10 ,  F04B1/16 ,  F04B17/03 ,  F05D2240/24

    Abstract: The present invention provides a method and system for providing on-site electrical power to a fracturing operation, and an electrically powered fracturing system. Natural gas can be used to drive a turbine generator in the production of electrical power. A scalable, electrically powered fracturing fleet is provided to pump fluids for the fracturing operation, obviating the need for a constant supply of diesel fuel to the site and reducing the site footprint and infrastructure required for the fracturing operation, when compared with conventional systems. The treatment fluid can comprise a water-based fracturing fluid or a waterless liquefied petroleum gas (LPG) fracturing fluid.

    Abstract translation: 本发明提供了一种用于向压裂作业提供现场电力的方法和系统，以及电动压裂系统。 天然气可用于驱动涡轮发电机生产电力。 提供可扩展的电动压裂机组，用于泵送压裂作业的流体，避免了与常规系统相比，需要向现场持续供应柴油，并减少压裂作业所需的现场占地面积和基础设施。 处理流体可以包括水基压裂液或无水液化石油气（LPG）压裂液。

    SHAPED RIM CAVITY WING SURFACE
    85.
    发明申请
    SHAPED RIM CAVITY WING SURFACE 有权
    形状RIM CAVITY WING SURFACE

    公开(公告)号：US20130294897A1

    公开(公告)日：2013-11-07

    申请号：US13462150

    申请日：2012-05-02

    Applicant: Eric A. Grover

    Inventor： Eric A. Grover

    IPC: F01D11/00

    CPC classification number: F01D11/001 ,  F01D5/02 ,  F01D9/041 ,  F01D11/003 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/55

    Abstract: A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.

    Abstract translation: 成型的边缘腔翼包括上表面和下表面。 下表面具有几何形状以控制气流在下表面到顶面周围的分离。 最大程度的一点限定了上表面和下表面之间的边界，其中最大程度的点限定了将气流与成形的边缘空腔边缘分离的角部，并且产生邻近于顶部表面的流动再循环 形轮缘腔翼。

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