中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

318 records (took 0.072 seconds)

    Welded low-pressure turbine shaft
    131.
    发明授权
    Welded low-pressure turbine shaft 有权
    焊接低压涡轮轴

    公开(公告)号：US08083492B2

    公开(公告)日：2011-12-27

    申请号：US12227468

    申请日：2007-02-23

    Applicant: Torsten-Ulf Kern

    Inventor： Torsten-Ulf Kern

    IPC: F01D5/02

    CPC classification number: F01D5/063 ,  C22C38/04 ,  C22C38/44 ,  C22C38/46 ,  F01D5/28 ,  F05C2201/0466 ,  F05D2300/131 ,  F05D2300/132 ,  Y10S464/902

    Abstract: Turbo-engine which has a low-pressure area, containing at least one shaft, wherein the low-pressure area has an inflow area, the shaft having, at least on its inflow part arranged in the inflow area, a heat resistant material, wherein the shaft has, on outflow parts arranged opposite the inflow part, a 26NiCrV14-5 and/or 2SNiCrMoVii-5 and/or 22CrNiM09-9 material.

    Abstract translation: 具有低压区域的涡轮发动机，其包含至少一个轴，其中所述低压区域具有流入区域，所述轴至少在其流入部分中布置在流入区域中，具有耐热材料，其中 轴在与流入部分相对的流出部分上具有26NiCrV14-5和/或2SNiCrMoVii-5和/或22CrNiM09-9材料。

    Component for a gas turbine and a method for the production of the component
    132.
    发明申请
    Component for a gas turbine and a method for the production of the component 有权
    用于燃气轮机的组件和用于生产组件的方法

    公开(公告)号：US20110305578A1

    公开(公告)日：2011-12-15

    申请号：US12998411

    申请日：2009-10-14

    Applicant: Wilfried Smarsly ,  Joerg Esslinger

    Inventor： Wilfried Smarsly ,  Joerg Esslinger

    IPC: F01D5/14 ,  B23P15/02

    CPC classification number: F01D5/34 ,  B23K20/1205 ,  B23K2101/001 ,  B23K2103/14 ,  B23P15/006 ,  F05B2230/239 ,  F05C2201/0466 ,  F05D2230/50 ,  F05D2300/133 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49968

    Abstract: A component for a gas turbine, especially a blisk or a bling, whereby the component includes a rotor base (12) made of a high temperature-resistant nickel alloy and a plurality of turbine blades (14) joined to the rotor base, whereby each turbine blade includes a rotor blade (16) made of a titanium alloy and a blade root. The blade root is configured as an adapter element (18) that is made of a material that can be welded to the titanium alloy as well as to the high temperature-resistant nickel alloy and that is integrally joined to the rotor base (12) and to the rotor blade (16) fusion. A method for the production of the component is also described.

    Abstract translation: 一种用于燃气轮机的部件，特别是叶片或叶片，其中部件包括由耐高温镍合金制成的转子基座（12）和与转子基座接合的多个涡轮机叶片（14），由此 涡轮叶片包括由钛合金和叶片根部制成的转子叶片（16）。 叶片根部被配置为由能够焊接到钛合金以及耐高温镍合金并且与转子基座（12）整体接合的材料制成的适配器元件（18），并且 到转子叶片（16）的融合。 还描述了用于制造组件的方法。

    METHOD FOR PROVIDING RUB COATINGS FOR GAS TURBINE ENGINE COMPRESSORS
    133.
    发明申请
    METHOD FOR PROVIDING RUB COATINGS FOR GAS TURBINE ENGINE COMPRESSORS 审中-公开
    用于燃气涡轮发动机压缩机的润滑油涂层的方法

    公开(公告)号：US20110302781A1

    公开(公告)日：2011-12-15

    申请号：US13214842

    申请日：2011-08-22

    Applicant: Albert S. DODD, IV ,  Thomas John Tomlinson ,  William R. Rossey, JR.

    Inventor： Albert S. DODD, IV ,  Thomas John Tomlinson ,  William R. Rossey, JR.

    IPC: B23P6/00

    CPC classification number: F01D11/122 ,  B23P6/007 ,  C23C4/073 ,  C23C30/00 ,  F01D5/005 ,  F01D5/286 ,  F01D5/288 ,  F05C2201/0466 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2260/95 ,  F05D2300/15 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/673 ,  Y10T29/49318

    Abstract: Rub coatings, and methods for applying rub coatings, are provided for compressor assemblies of gas turbine engine assemblies. The coating may be applied as an initial coating to a new surface of a component, as well as a repair and replacement corrosion resistant rub coating for applying to a previously coated component of a gas turbine engine assembly such as a compressor casing. The method includes the steps of providing a component of a gas turbine engine assembly, the component having predetermined dimensions and specifications for operational use in an engine assembly. The component has a surface having a damaged rub coating thereon, the damaged rub coating not in compliance with the predetermined dimensions and specifications. The method includes removing the non-compliant damaged rub coating to expose the surface. Next, a repair corrosion resistant rub coating comprising MCrAlX is applied to the surface. Finally, the repair corrosion resistant rub coating comprising MCrAlX is machined to restore the coated component to comply with the predetermined dimensions and specifications.

    Abstract translation: 提供了用于燃气涡轮发动机组件的压缩机组件的摩擦涂层和用于涂覆摩擦涂层的方法。 涂层可以作为初始涂层施加到部件的新表面，以及用于施加到诸如压缩机壳体的燃气涡轮发动机组件的预先涂覆的部件的修复和替换耐腐蚀摩擦涂层。 该方法包括提供燃气涡轮发动机组件的部件的步骤，该部件具有用于发动机组件中的操作使用的预定尺寸和规格。 该组件具有在其上具有损坏的摩擦涂层的表面，损坏的擦拭涂层不符合预定的尺寸和规格。 该方法包括去除不顺应损坏的摩擦涂层以暴露表面。 接下来，将包含MCrAlX的修复耐腐蚀的摩擦涂层施加到表面。 最后，加工包含MCrAlX的修复耐腐蚀的摩擦涂层，以恢复涂覆的部件以符合预定的尺寸和规格。

    Sealed systems and methods for sealing a shaft
    134.
    发明授权
    Sealed systems and methods for sealing a shaft 有权
    用于密封轴的密封系统和方法

    公开(公告)号：US07946593B2

    公开(公告)日：2011-05-24

    申请号：US11742163

    申请日：2007-04-30

    Applicant: Mohsiul Alam ,  Jack Moy ,  Thomas P. Swadener ,  James E. Franks

    Inventor： Mohsiul Alam ,  Jack Moy ,  Thomas P. Swadener ,  James E. Franks

    IPC: F16J15/02 ,  F16L55/10 ,  F01D11/00

    CPC classification number: F01D11/003 ,  F01D25/183 ,  F05C2201/0466 ,  F16J15/0887

    Abstract: A seal is provided for sealing a hollow shaft, where the hollow shaft has an inner surface that may be uneven due to shot peening. The seal includes an axially extending ring section having a first end, a second end, an inner surface, and a disk section disposed substantially perpendicular to the ring section inner surface between the ring section first and second ends. The seal conforms to the shaft inner surface to stop oil leakage.

    Abstract translation: 提供用于密封空心轴的密封件，其中空心轴具有由于喷丸硬化而可能不均匀的内表面。 密封件包括轴向延伸的环形部分，其具有第一端，第二端，内表面和与环部分第一端和第二端之间的环部分内表面基本垂直的基板。 密封件符合轴内表面，以防止漏油。

    Component having a coating
    138.
    发明授权
    Component having a coating 有权
    具有涂层的组分

    公开(公告)号：US07655321B2

    公开(公告)日：2010-02-02

    申请号：US11210034

    申请日：2005-08-23

    Applicant: Anton Albrecht ,  Thomas Cosack ,  Thomas Dautl ,  Horst Pillhoefer

    Inventor： Anton Albrecht ,  Thomas Cosack ,  Thomas Dautl ,  Horst Pillhoefer

    IPC: B32B15/00 ,  B32B15/01 ,  C25D7/00

    CPC classification number: F01D5/288 ,  C23C10/16 ,  C23C10/58 ,  C23C28/042 ,  C23C28/048 ,  F05C2201/0466 ,  F05D2300/121 ,  F05D2300/143 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12736 ,  Y10T428/1275 ,  Y10T428/12875

    Abstract: A component having a corrosion-resistant and/or oxidation-resistant coating is provided that includes at least one platinum-aluminum substrate area is provided, the component having a substrate surface (11) and a substrate composition based on nickel, with a platinum-aluminum substrate area (12) formed in the area of the substrate surface of the component by precipitating platinum (Pt) and aluminum (Al) on the substrate surface. The platinum-aluminum substrate area (12) has a two-phase structure or duplex structure with finely dispersed platinum-aluminum deposits in a nickel-based mixed crystal in an outer zone (13), and a single-phase structure made of a nickel-based mixed crystal in an inner zone (14) located between the substrate surface (11) of the component and the outer zone (13).

    Abstract translation: 提供了具有耐腐蚀和/或抗氧化涂层的部件，其包括提供至少一个铂 - 铝基底区域，所述部件具有基底表面（11）和基于镍的基底组合物， 通过在基板表面上沉淀铂（Pt）和铝（Al），形成在部件的基板表面区域中的铝基板区域（12）。 铂 - 铝基板区域（12）具有在外部区域（13）中的镍基混合晶体中具有精细分散的铂 - 铝沉积物的两相结构或双相结构，并且由镍制成的单相结构 基于位于所述部件的所述基板表面（11）和所述外部区域（13）之间的内部区域（14）中的所述混合晶体。

    Cooling arrangement for CMC components with thermally conductive layer
    139.
    发明授权
    Cooling arrangement for CMC components with thermally conductive layer 失效
    具有导热层的CMC部件的冷却布置

    公开(公告)号：US07641440B2

    公开(公告)日：2010-01-05

    申请号：US11514745

    申请日：2006-08-31

    Applicant: Jay A. Morrison ,  Jay E. Lane

    Inventor： Jay A. Morrison ,  Jay E. Lane

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/288 ,  F01D25/12 ,  F05C2201/0466 ,  F05D2260/201 ,  F05D2300/122 ,  F05D2300/141 ,  F05D2300/172 ,  F05D2300/222 ,  F05D2300/224 ,  F05D2300/2262 ,  F05D2300/5024 ,  F05D2300/603 ,  F23R3/007 ,  F23R2900/03044

    Abstract: A CMC wall (22) with a front surface (21) heated (24) by a working fluid in a gas turbine. A back CMC surface (23) is coated with a layer (42) of a thermally conductive material to accelerate heat transfer in the plane of the CMC wall (22), reducing thermal gradients (32-40) on the back CMC surface (23) caused by cold spots (32) resulting from impingement cooling flows (26). The conductive material (42) may have a coefficient of thermal conductivity at least 10 times greater than that of the CMC material (22), to provide a minimal thickness conductive layer (42). This reduces thermal gradient stresses within the CMC material (22), and minimizes differential thermal expansion stresses between the CMC material (22) and the thin conductive layer (42).

    Abstract translation: 具有通过燃气轮机中的工作流体加热（24）的前表面（21）的CMC壁（22）。 背部CMC表面（23）涂覆有导热材料层（42），以加速在CMC壁（22）的平面中的热传递，从而降低背面CMC表面（23）上的热梯度（32-40） ）由冲击冷却流产生的冷点（32）引起（26）。 导电材料（42）的导热系数可以比CMC材料（22）的导热系数高至少10倍，以提供最小厚度的导电层（42）。 这降低了CMC材料（22）内的热梯度应力，并且使CMC材料（22）和薄导电层（42）之间的差热膨胀应力最小化。

Patent Agency Ranking