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    TURBINE ENGINE COMPONENT WITH DIFFUSER HOLES
    41.
    发明申请
    TURBINE ENGINE COMPONENT WITH DIFFUSER HOLES 审中-公开
    涡轮发动机组件与扩口阀

    公开(公告)号：US20160273364A1

    公开(公告)日：2016-09-22

    申请号：US14661975

    申请日：2015-03-18

    申请人： General Electric Company

    发明人： Robert Frederick BERGHOLZ

    IPC分类号： F01D5/18 ,  F01D9/06

    CPC分类号： F01D5/186 ,  F01D9/065 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/21 ,  F05D2250/23 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042

    摘要： A turbine component includes a component wall with inner and outer surfaces wherein a diffuser hole passes through the component wall between the inner surface and the outer surface. The diffuser hole has a hole axis and includes: a metering section extending from an inlet at the inner surface to a junction plane between the inner and outer surfaces; and a diffuser section extending from the junction plane to an outlet at the outer surface, and increasing in flow area from the junction plane to the outlet, the diffuser section having an upstream portion defining a first area ratio and a downstream portion defining a second area ratio different from the second area ratio.

    摘要翻译： 涡轮机部件包括具有内表面和外表面的部件壁，其中扩散器孔穿过内表面和外表面之间的部件壁。 扩散器孔具有孔轴，包括：从内表面的入口延伸到内表面和外表面之间的接合面的计量部分; 以及扩散器部分，其从所述接合平面延伸到所述外表面处的出口，并且从所述接合面到所述出口的流动面积增加，所述扩散器部分具有限定第一面积比的上游部分和限定第二面积的下游部分 比率与第二面积比不等。

    Cast Features for Location and Inspection
    42.
    发明申请
    Cast Features for Location and Inspection 审中-公开
    地理位置和检查的演员特征

    公开(公告)号：US20150239043A1

    公开(公告)日：2015-08-27

    申请号：US14185986

    申请日：2014-02-21

    申请人： Siemens Energy, Inc.

    发明人： Jonathan E. Shipper, JR. ,  Samuel R. Miller, JR. ,  Jae Y. Um ,  Michael E. Crawford ,  Gary B. Merrill ,  Ahmed Kamel

    IPC分类号： B22D46/00 ,  B22D25/02

    CPC分类号： B22D46/00 ,  B22C7/02 ,  F01D21/003 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2250/131 ,  F05D2250/20 ,  F05D2250/21 ,  F05D2250/22 ,  F05D2250/221 ,  F05D2250/23 ,  F05D2250/231

    摘要： A method for casting an object (12) having an integrated surface feature (10) for location, inspection, and analysis using a feature-based vision system is provided herein that includes determining a shape geometry for a surface feature (10), wherein the shape geometry is adapted for tracking with a feature-based vision system, determining a proper size, placement, and orientation for the surface feature (10) based on a type of inspection, and casting the surface feature (10) into an object (12) at the determined placement and orientation using an investment casting process to produce an integrated surface feature. An object manufactured in accordance with this casting method wherein the object comprises an integrated surface feature (10) for location, inspection, and analysis using a feature-based vision system is also provided

    摘要翻译： 本文提供了一种用于铸造具有用于使用基于特征的视觉系统进行定位，检查和分析的集成表面特征（10）的物体（12）的方法，其包括确定表面特征（10）的形状几何形状，其中， 形状几何适于使用基于特征的视觉系统进行跟踪，基于检查的类型确定表面特征（10）的适当大小，位置和取向，以及将表面特征（10）投射到物体（12）中 ）以确定的放置和取向使用熔模铸造工艺来产生集成的表面特征。 还提供了根据该铸造方法制造的物体，其中所述物体包括用于使用基于特征的视觉系统进行定位，检查和分析的综合表面特征（10）

    Turbine abradable layer with nested loop groove pattern
    43.
    发明授权
    Turbine abradable layer with nested loop groove pattern 有权
    具有嵌套环槽图案的涡轮磨损层

    公开(公告)号：US08939716B1

    公开(公告)日：2015-01-27

    申请号：US14189011

    申请日：2014-02-25

    申请人： Siemens Aktiengesellschaft

    发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Vincent P. Laurello ,  Gm Salam Azad ,  Nicholas F. Martin, Jr.

    IPC分类号： F01D11/08 ,  F01D11/12

    CPC分类号： F01D11/122 ,  F01D11/00 ,  F01D11/08 ,  F05D2240/11 ,  F05D2250/141 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/185 ,  F05D2250/23

    摘要： Turbine and compressor casing abradable component embodiments for turbine engines, with nested loop pattern abradable surface ridges and grooves. The nested loops comprise nested fully closed loops or a spiraling maze pattern loop. 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.

    摘要翻译： 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，具有嵌套的环形图案可磨损的表面脊和凹槽。 嵌套循环包括嵌套完全闭环或螺旋式迷宫模式循环。 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。

    BLADE FOR A GAS TURBINE
    46.
    发明申请
    BLADE FOR A GAS TURBINE 有权
    燃气轮机叶片

    公开(公告)号：US20110085915A1

    公开(公告)日：2011-04-14

    申请号：US12876602

    申请日：2010-09-07

    申请人： Joerg KRUECKELS ,  Roland DUECKERSHOFF ,  Martin SCHNIEDER

    发明人： Joerg KRUECKELS ,  Roland DUECKERSHOFF ,  Martin SCHNIEDER

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/23 ,  F05D2250/231 ,  F05D2260/2212 ,  Y02T50/676

    摘要： A blade for a gas turbine includes a leading edge running in a longitudinal direction substantially radially to an axis of the turbine; a trailing edge running in the longitudinal direction; a blade body disposed between the leading edge and the trailing edge so as to define a pressure side and a suction side; an exit slot disposed in the blade body in an area of the trailing edge and running in the longitudinal direction and configured to discharge a cooling medium from an interior of the blade body; and a row of first and second control elements disposed in the exit slot in a distributed manner in the longitudinal direction and configured to control a mass flow of the cooling medium exiting through the exit slot, the first control elements having a first configuration and the second control elements having a second configuration different from the first configuration.

    摘要翻译： 一种用于燃气轮机的叶片包括沿着基本上径向相对于涡轮轴线的纵向方向延伸的前缘; 沿纵向延伸的后缘; 刀片体，其设置在所述前缘和所述后缘之间，以限定压力侧和吸力侧; 出口狭槽，其设置在所述后缘的区域中并沿所述纵向方向延伸并且构造成从所述叶片本体的内部排出冷却介质; 以及一排第一和第二控制元件，其沿长度方向以分布的方式设置在出口槽中，并被配置为控制从出口槽排出的冷却介质的质量流量，第一控制元件具有第一配置，第二控制元件具有第二配置 控制元件具有不同于第一配置的第二配置。

    Blade Arrangement
    47.
    发明申请
    Blade Arrangement 有权
    刀片安排

    公开(公告)号：US20100021302A1

    公开(公告)日：2010-01-28

    申请号：US12515845

    申请日：2007-10-25

    申请人： Andreas Kayser

    发明人： Andreas Kayser

    IPC分类号： F01D5/26

    CPC分类号： F01D5/22 ,  F01D11/008 ,  F05D2250/23 ,  F05D2250/231 ,  Y10S416/50

    摘要： A blade arrangement with a rotor and a plurality of blades which are arranged on the periphery of the rotor in a ring and a plurality of damping elements are provided. Between two directly adjacent blades at least two damping elements are arranged in series in the circumferential direction of the rotor. As a result of a centrifugal force, which acts in the radial direction, during a rotation of the rotor around a rotor axis adjacent damping elements come into contact with each other, and one of the two damping elements comes into contact with one of the two blades and the other of the two damping elements comes into contact with the other of the two blades.

    摘要翻译： 提供了一种具有转子和多个叶片的叶片装置，它们设置在环上的转子周边和多个阻尼元件上。 在两个直接相邻的叶片之间，至少两个阻尼元件在转子的圆周方向上串联布置。 作为沿径向作用的离心力的结果是，在围绕转子轴线转动的转子轴线相邻的阻尼元件彼此接触时，两个阻尼元件中的一个与两个阻尼元件中的一个接触 叶片和两个阻尼元件中的另一个与两个叶片中的另一个接触。

    Damping and sealing system for turbine blades
    48.
    发明申请
    Damping and sealing system for turbine blades 审中-公开
    涡轮叶片阻尼和密封系统

    公开(公告)号：US20090136350A1

    公开(公告)日：2009-05-28

    申请号：US11896508

    申请日：2007-09-04

    申请人： Richard Whitton

    发明人： Richard Whitton

    IPC分类号： F01D5/30

    CPC分类号： F01D5/22 ,  F01D11/008 ,  F05D2240/80 ,  F05D2250/23 ,  F05D2250/71

    摘要： With a gas-turbine engine, a sealing and damping element (9), which is loosely held between two adjacent platforms (6a, 6b) of turbine blades attached to a rotor disk, generally has a cross-section in the form of a straight three sided prism corresponding to an equilateral triangle, however with convex rubbing surface sides. Due to small swiveling movements enabled by the curvature of the sides, an increased rubbing and wear area is created during operation, which is adapted to the blade geometry and can be determined in advance, thus increasing damping and sealing efficiency.

    摘要翻译： 利用燃气涡轮发动机，松动地保持在附接到转子盘的涡轮叶片的两个相邻平台（6a，6b）之间的密封和阻尼元件（9）通常具有直线形状的横截面 三面棱镜对应于等边三角形，然而凸面摩擦表面侧。 由于由侧面的曲率实现的小的旋转运动，在操作期间产生增加的摩擦和磨损面积，其适合于叶片几何形状并且可以预先确定，从而增加阻尼和密封效率。

    Curved variable pitch wedge retention in vane outer base
    50.
    发明申请
    Curved variable pitch wedge retention in vane outer base 有权
    叶片外基座中弯曲变桨距楔形保持

    公开(公告)号：US20080063521A1

    公开(公告)日：2008-03-13

    申请号：US11519637

    申请日：2006-09-12

    申请人： William Bogue ,  Bruce A. McCollum

    发明人： William Bogue ,  Bruce A. McCollum

    IPC分类号： F04D29/54

    CPC分类号： F04D29/542 ,  F01D5/005 ,  F01D9/042 ,  F04D29/644 ,  F05D2230/23 ,  F05D2250/23 ,  F05D2250/292 ,  F05D2250/71 ,  Y10T29/49236

    摘要： A method for repairing or replacing a mechanically retained vane is provided. The method comprises the steps of forming an oversized cavity in an outer base, inserting a flared end of a vane in the oversized cavity, and inserting a wedge for mechanically retaining the flared end of the vane in the oversized cavity. The wedge has a first surface with a constant pitch angle to match the outer base cavity and a second surface with a variable pitch angle to match the vane tip dovetail.

    摘要翻译： 提供了修复或更换机械保持叶片的方法。 该方法包括以下步骤：在外部基座中形成一个过大的空腔，将一个叶片的扩口端插入超大空腔中，以及插入楔形件，用于将叶片的扩口端机械地保持在尺寸过大的腔体中。 楔具有具有恒定桨距角的第一表面以匹配外基腔和具有可变桨距角的第二表面以匹配叶片尖端燕尾形。