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498 条记录 (耗时 0.022 秒)

    Workpiece clamp device with single side
    1.
    发明授权
    Workpiece clamp device with single side 有权

    公开(公告)号：US09844855B1

    公开(公告)日：2017-12-19

    申请号：US15188458

    申请日：2016-06-21

    申请人： Po-Shen Chen

    发明人： Po-Shen Chen

    IPC分类号： B25B1/08 ,  B25B1/10 ,  F01D5/32 ,  F01D5/30 ,  F16M7/00

    CPC分类号： B25B1/08 ,  B25B1/10 ,  B25B1/2405 ,  F01D5/3038 ,  F01D5/32 ,  F01D5/323 ,  F16M7/00

    摘要： A workpiece clamp device with single side is disclosed. When a bolt is screwed in relative to a base plane, an elastic member is compressed by a first and a second stop portions and a second clamp surface of a driving block is limited by a second wall surface. A first inclined surface is pushed leftward by a second inclined surface so that a tool is clamped by the first clamp surface and a first wall surface. When the bolt is screwed out relative to the base plane, the elastic member is reset due to the compression of the first and the second stop portions. Since the second clamp surface is limited by a second wall surface, the first inclined surface is pushed rightward by the second inclined surface to move the driving block upward so that the force for clamping the tool is released and the tool is disassembled.

    GAS TURBINE ENGINE BLADE PLATFORM MODIFICATION
    2.
    发明申请
    GAS TURBINE ENGINE BLADE PLATFORM MODIFICATION 审中-公开
    气体涡轮发动机叶片平台修改

    公开(公告)号：US20170074281A1

    公开(公告)日：2017-03-16

    申请号：US14854237

    申请日：2015-09-15

    申请人： General Electric Company

    发明人： Qiang Li ,  Aaron Phillip King ,  Toby George Darkins, JR. ,  Anthony Joseph Maurer

    IPC分类号： F04D29/32 ,  F01D5/30 ,  F04D29/66

    CPC分类号： F04D29/324 ,  F01D5/14 ,  F01D5/26 ,  F01D5/303 ,  F01D5/3038 ,  F04D29/668 ,  F05B2240/80 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2250/712 ,  F05D2260/96 ,  Y02T50/673

    摘要： A gas turbine engine compressor blade includes an airfoil and a root section connected to a blade platform therebetween and an at least partially curved cropped corner of the blade platform. The corner shape and size may avoid resonance of blade during engine operation. Corner may be J-shaped including a straight section extending from pressure side edge towards suction side edge of platform and curved section extending from straight section to uncropped portion of platform trailing edge of the platform. A method of designing the cropped corner includes choosing shapes sizes of the cropped corner for numerically analyzing and determining shape and size for cropped corner using numerical model to iteratively numerically analyze aerodynamically cropped platform with different shapes and sizes of cropped corner. Numerical model may be validated with engine or component testing of blade having a cropped platform with at least one of the shapes and sizes.

    摘要翻译： 燃气涡轮发动机压缩机叶片包括翼型件和连接到它们之间的叶片平台的根部部分和刀片平台的至少部分弯曲的裁剪角部。 角形和尺寸可以避免发动机运转时叶片的共振。 角部可以是J形，包括从压力侧边缘朝向平台的吸力侧边缘延伸的直线部分，以及从平台的直线部分延伸到平台后缘的未裁剪部分的弯曲部分。 设计裁剪角的方法包括选择裁剪角的形状大小进行数值分析，并使用数值模型确定裁剪角的形状和尺寸，以迭代数值分析具有不同形状和尺寸的裁剪角的空气动力学裁剪平台。 数值模型可以用具有具有至少一种形状和尺寸的裁剪平台的叶片的发动机或部件测试来验证。

    Gas turbine engine compressor rotor assembly and balancing system
    3.
    发明授权
    Gas turbine engine compressor rotor assembly and balancing system 有权
    燃气涡轮发动机压缩机转子总成和平衡系统

    公开(公告)号：US09404367B2

    公开(公告)日：2016-08-02

    申请号：US13684056

    申请日：2012-11-21

    申请人： Solar Turbines Incorporated

    发明人： Cory Patrick Muscat ,  Laura Elizabeth McDonald ,  James Eric Miller ,  Gary Paul Vavrek

    IPC分类号： F01D5/02 ,  F01D5/06 ,  F01D5/30

    CPC分类号： F01D5/027 ,  F01D5/06 ,  F01D5/3015 ,  F01D5/3038

    摘要： A method for balancing a compressor rotor assembly including a forward weldment (211) and an aft weldment (212) includes pre-balancing the aft weldment (212) of the compressor rotor assembly (210) with compressor disks (220) prior to populating the compressor disks (220) with circumferentially installed compressor rotor blades (230). Pre-balancing the aft weldment (212) includes measuring a rotational balance of the aft weldment (212). Pre-balancing the aft weldment (212) also includes determining a number of underplatform weights (260) needed and a location for each underplatform weight (260) within a circumferential slot (236) of one the compressor disks (220). Pre-balancing the aft weldment (212) further includes mounting each underplatform weight (260) in the determined location.

    摘要翻译： 一种用于平衡包括前向焊接件（211）和后部焊件（212）的压缩机转子组件的方法包括：在压缩机转子组件（210）的后部焊件（212）与压缩机盘（220）预先平衡之前， 具有周向安装的压缩机转子叶片（230）的压缩机盘（220）。 预平衡后焊件（212）包括测量后焊件（212）的旋转平衡。 预平衡船尾焊件（212）还包括确定在压缩机盘（220）之一的圆周槽（236）内的所需的底板数量（260）和每个底板下重量（260）的位置。 预平衡船尾焊件（212）还包括将每个底板重量（260）安装在所确定的位置。

    AEROFOIL BLADE
    6.
    发明申请
    AEROFOIL BLADE 有权
    AEROFOIL刀片

    公开(公告)号：US20150300181A1

    公开(公告)日：2015-10-22

    申请号：US14451690

    申请日：2014-08-05

    申请人： ROLLS-ROYCE PLC

    发明人： Mark John KNIGHT

    IPC分类号： F01D5/30 ,  F01D5/14

    CPC分类号： F01D5/3038 ,  F01D5/141 ,  F01D5/30 ,  F01D11/16 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2240/30

    摘要： A turbomachine aerofoil blade has an aerofoil body portion and a dovetail root fixing at the base of the aerofoil body portion which slides, in use, into a correspondingly shaped slot of a rotor of the turbomachine. The dovetail root fixing has a neck portion, and support flanks engage with matching angled surfaces of the slot under centrifugal loading of the aerofoil blade to support the aerofoil blade on the rotor. The neck portion is shaped such that a rotational adjustment of the aerofoil blade relative to its angular position when supported under centrifugal loading is needed to provide adequate clearance at the neck portion to allow the dovetail root fixing to slide into the slot. On centrifugal loading the engagement of the support flanks with the matching angled surfaces of the slot forces a reversal of the rotational adjustment and reduces the clearance at the neck portion.

    摘要翻译： 涡轮机翼型叶片具有机翼部分和燕尾根部固定在机翼本体部分的基部，其在使用中滑动到涡轮机的转子的相应形状的槽中。 燕尾根固定具有颈部，并且在机翼叶片的离心负载下，支撑侧面与槽的匹配的成角度的表面接合，以支撑转子上的机翼叶片。 颈部被成形为使得当在离心负载下被支撑时，翼面叶片相对于其角位置的旋转调节需要在颈部处提供足够的间隙，以允许燕尾根固定件滑入槽中。 在离心加载时，支撑侧面与槽的匹配的成角度的表面的接合迫使旋转调节的反转并减小颈部处的间隙。

    Turbine bucket including an integral rotation controlling feature
    8.
    发明授权
    Turbine bucket including an integral rotation controlling feature 有权
    涡轮斗包括一体式旋转控制功能

    公开(公告)号：US09057278B2

    公开(公告)日：2015-06-16

    申请号：US13591278

    申请日：2012-08-22

    申请人： James Royce Howes ,  Mark Kevin Bowen ,  Robert James Bracken ,  Laurence Scott Duclos ,  Scott Leroy Irwin ,  Nicholas Andrew Tisenchek

    发明人： James Royce Howes ,  Mark Kevin Bowen ,  Robert James Bracken ,  Laurence Scott Duclos ,  Scott Leroy Irwin ,  Nicholas Andrew Tisenchek

    IPC分类号： F01D5/30 ,  F01D5/22

    CPC分类号： F01D5/3038 ,  F01D5/225 ,  Y02E20/16

    摘要： A turbine bucket including an integral rotation controlling feature is disclosed. In one embodiment, a turbine bucket includes: a blade section having an inner radial end and an outer radial end; an integral cover section connected to the outer radial end of the blade section; and a base section for engaging a rotor body, the base section connected to the inner radial end, wherein the base section includes: a central body; a set of tangs extending axially from the central body; a set of flanges radially inboard of the set of tangs and extending axially from the central body; and an integral rotation controlling feature extending from the central body, wherein the rotation controlling feature engages a radial opening in the rotor body. The integral rotation controlling feature is sized to limit rotation of the base section, when the turbine bucket is engaged with a rotor body.

    摘要翻译： 公开了一种包括一体旋转控制特征的涡轮机叶片。 在一个实施例中，涡轮机桶包括：具有内径向端和外径向端的叶片部分; 连接到所述叶片部分的外径向端部的整体覆盖部分; 以及用于接合转子体的基部，所述基部连接到所述内径向端，其中所述基部包括：中心体; 一组从中心体轴向延伸的柄脚; 一组凸缘，径向地设置在一组柄脚的内侧，并从中心体轴向延伸; 以及从所述中心体延伸的一体旋转控制特征，其中所述旋转控制特征与所述转子体中的径向开口接合。 整体旋转控制特征的尺寸被限制为当涡轮机叶片与转子体接合时，限制基部的旋转。

    Rotor of a turbomachine
    9.
    发明申请
    Rotor of a turbomachine 审中-公开
    涡轮机转子

    公开(公告)号：US20150139808A1

    公开(公告)日：2015-05-21

    申请号：US14546699

    申请日：2014-11-18

    申请人： MTU Aero Engines AG

    发明人： Alexander Kloetzer ,  Dieter Hofmann

    IPC分类号： F01D5/30

    CPC分类号： F01D5/3038 ,  F01D5/32

    摘要： A rotor of a turbomachine. The rotor includes at least one blade (4, 6, 8) that has a blade leaf (20) and a blade root (54, 55, 58), and a rotor base body (2), in particular a disk (2), that has an outwardly open, circumferential groove (12) for receiving the blade root (54, 55, 58). The circumferential groove (12) and the blade root (54, 55, 58) are shaped in a way that allows the blade root (54, 55, 58) to be secured in the circumferential groove (12) by the rotation of the blade (4, 6, 8) about an axis (Ar, AT).

    摘要翻译： 涡轮机的转子。 转子包括具有叶片叶片（20）和叶片根部（54,55,58）和转子基体（2），特别是盘（2）的至少一个叶片（4,6,8） ，其具有用于接收叶片根部（54,55,58）的向外开口的圆周凹槽（12）。 圆周沟槽（12）和叶片根部（54,55,58）的形状可以通过叶片的旋转将叶片根部（54,55,58）固定在周向槽（12）中， （4,6,8）围绕轴线（Ar，AT）。

    LOCKING SPACER ASSEMBLY
    10.
    发明申请
    LOCKING SPACER ASSEMBLY 有权
    锁定间隔装置

    公开(公告)号：US20150101351A1

    公开(公告)日：2015-04-16

    申请号：US14055124

    申请日：2013-10-16

    申请人： General Electric Company

    发明人： Michael James Healy ,  Brian Denver Potter

    IPC分类号： F01D5/30

    CPC分类号： F01D5/303 ,  F01D5/3038 ,  F01D5/32

    摘要： Locking spacer assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a spacer, the spacer including a platform and a plurality of legs extending generally radially inward from the platform. The locking spacer assembly further includes a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other. The locking spacer assembly further includes a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.

    摘要翻译： 提供了锁定间隔件组件和涡轮机。 在一个实施例中，锁定间隔件组件包括间隔件，间隔件包括平台和从平台大致径向向内延伸的多个腿。 锁定间隔件组件还包括夹具，该夹具构造成使多个腿中的每一个在大致轴向方向上彼此接触并引起弹性变形。 锁定间隔件组件还包括锁定凸耳，所述锁定凸耳构造成在相反的大致轴向方向上接触并向所述多个支腿中的每一个施加力。