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    Systems for preventing wear on turbine blade tip shrouds
    21.
    发明申请
    Systems for preventing wear on turbine blade tip shrouds 有权
    用于防止涡轮叶片尖端罩磨损的系统

    公开(公告)号：US20080145207A1

    公开(公告)日：2008-06-19

    申请号：US11638818

    申请日：2006-12-14

    Applicant: Patrick Mohr ,  Daniel Nowak ,  Emilio Fernandez ,  Michael Arnett ,  David Williams ,  Carlos Collado

    Inventor： Patrick Mohr ,  Daniel Nowak ,  Emilio Fernandez ,  Michael Arnett ,  David Williams ,  Carlos Collado

    IPC: F01D11/12 ,  F04D29/08

    CPC classification number: F01D5/225 ,  F05C2201/0463 ,  F05D2300/506

    Abstract: A system in a turbine engine for preventing wear on a tip shroud of a turbine blade that includes a pocket formed in a contact surface of the tip shroud and a plug that fits within the pocket and has a durable outer surface. The durable outer surface may include a cobalt-based hardfacing powder. The pocket may be machined out of the contact surface, and the plug may include a plug of predetermined size that fits snugly into the pocket. In some embodiments, the durable outer surface may substantially align with the contact surface after the plug is fitted into the pocket. In other embodiments, the durable outer surface may remain slightly raised from the contact surface after the plug has been fitted into the pocket.

    Abstract translation: 一种涡轮发动机中的系统，用于防止涡轮机叶片的尖端护罩上的磨损，该系统包括形成在尖端护罩的接触表面中的凹穴和装配在口袋内并且具有耐用的外表面的塞子。 耐用的外表面可以包括钴基硬化粉末。 口袋可以从接触表面加工出来，并且塞子可以包括预先规定尺寸的塞子，该栓塞紧贴地配合到口袋中。 在一些实施例中，在将塞子装配到口袋中之后，耐用的外表面可以与接触表面大致对准。 在其他实施例中，在插头已经装配到口袋中之后，耐用的外表面可以保持从接触表面稍微升高。

    High temperature and high pressure compressor piston ring
    24.
    发明申请
    High temperature and high pressure compressor piston ring 有权
    高温高压压缩机活塞环

    公开(公告)号：US20050109289A1

    公开(公告)日：2005-05-26

    申请号：US10719223

    申请日：2003-11-21

    Applicant: Yoshio Usui ,  Tom Iles ,  Trung Tran

    Inventor： Yoshio Usui ,  Tom Iles ,  Trung Tran

    IPC: F04B39/00 ,  F16J9/14 ,  F16J9/20 ,  F16J9/26 ,  F02B75/00

    CPC classification number: F04B39/0005 ,  F05C2201/0406 ,  F05C2201/0463 ,  F05C2203/0808 ,  F05C2203/0826 ,  F16J9/14 ,  F16J9/20 ,  F16J9/26

    Abstract: A piston ring for use at temperatures above 350° F. at pressures greater than or equal to about 2000 psi, comprising a gap having a gap width about 1.4 to about 2.0 times greater than a thickness of the piston ring; a height about 4.5 to about 6.4 times larger than the thickness, and a leading edge characterized by an arc having a radius of curvature of less than or equal to about 4 times the height. The piston ring may be formed of a material comprising cobalt, chromium, tungsten, and carbon. A gas compressor and method of sealing a piston using the above piston ring is also provided for.

    Abstract translation: 一种在大于或等于约2000psi的压力下在高于350°F的温度下使用的活塞环，包括间隙宽度比活塞环厚度大约1.4至大约2.0倍的间隙; 高度比该厚度大约4.5至大约6.4倍的高度，以及具有小于或等于大约4倍的曲率半径的弧形的前缘。 活塞环可以由包括钴，铬，钨和碳的材料形成。 还提供了一种气体压缩机和使用上述活塞环密封活塞的方法。

    Moving blade for a turbomachine and turbomachine
    25.
    发明申请
    Moving blade for a turbomachine and turbomachine 失效
    用于涡轮机和涡轮机的移动叶片

    公开(公告)号：US20030185685A1

    公开(公告)日：2003-10-02

    申请号：US10379987

    申请日：2003-03-05

    Inventor： Volker Simon

    IPC: F03B003/12

    CPC classification number: F01D5/147 ,  B22F2998/00 ,  F01D5/28 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2260/203 ,  F05D2300/612 ,  B22F7/006

    Abstract: A novel blade configuration does not exceed the permitted stresses for particular loads, especially as a result of centrifugal forces and which at the same time, allows the turbomachine to function with a high degree of efficiency. To this end, a moving blade for the turbomachine contains at least partially a cellular material, especially a foamed metal. The cellular material can be provided e.g. in the hollowed-out part of the moving blade.

    Abstract translation: 新颖的叶片结构不会超过特定载荷的允许应力，特别是由于离心力而同时允许涡轮机以高效率起作用。 为此，用于涡轮机的移动叶片至少部分地包含多孔材料，特别是泡沫金属。 细胞材料可以例如提供。 在动叶片的中空部分。

    Article protected by thermal barrier coating having a sintering inhibitor, and its fabrication
    26.
    发明申请
    Article protected by thermal barrier coating having a sintering inhibitor, and its fabrication 有权
    由具有烧结抑制剂的热障涂层保护的制品及其制造

    公开(公告)号：US20030077477A1

    公开(公告)日：2003-04-24

    申请号：US10086150

    申请日：2001-10-22

    Inventor： Robert William Bruce ,  Nicholas Hamilton Burlingame

    IPC: C03C027/02 ,  B32B015/04

    CPC classification number: C23C28/321 ,  C23C4/18 ,  C23C14/083 ,  C23C14/58 ,  C23C16/045 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  C23C30/00 ,  F01D5/288 ,  F05C2201/0463 ,  F05D2230/90 ,  F05D2300/161 ,  F05D2300/2112 ,  F05D2300/611 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12875 ,  Y10T428/12944

    Abstract: An article protected by a thermal barrier coating system includes a substrate having a substrate surface, and a thermal barrier coating system overlying the substrate. The thermal barrier coating system has a thermal barrier coating formed of a thermal barrier coating material arranged as a plurality of columnar grains extending generally perpendicular to the substrate surface and having grain surfaces. A sintering inhibitor is within the columnar grains, either uniformly distributed or concentrated at the grain surfaces. The sintering inhibitor is lanthanum oxide, lanthanum chromate, chromium oxide, and/or yttrium chromate, mixtures thereof, mixtures thereof with aluminum oxide, modifications thereof wherein cobalt or manganese is substituted for chromium, precursors thereof, and reaction products thereof.

    Abstract translation: 由热障涂层系统保护的物品包括具有基底表面的基底和覆盖基底的热障涂层系统。 热障涂层系统具有由隔热涂层材料形成的热障涂层，所述热障涂层布置为大致垂直于基板表面延伸并具有晶粒表面的多个柱状晶粒。 烧结抑制剂在柱状晶粒内，均匀分布或集中在晶粒表面。 烧结抑制剂是氧化镧，铬酸镧，氧化铬和/或铬酸钇，它们的混合物，与氧化铝的混合物，其中钴或锰代替铬的前体及其反应产物。

    Lubricating system for thermal medium delivery parts in a gas turbine
    27.
    发明授权
    Lubricating system for thermal medium delivery parts in a gas turbine 失效
    燃气轮机中热介质输送部件的润滑系统

    公开(公告)号：US06422818B2

    公开(公告)日：2002-07-23

    申请号：US09769749

    申请日：2001-01-26

    Applicant: Thomas Charles Mashey

    Inventor： Thomas Charles Mashey

    IPC: F01D508

    CPC classification number: C23C28/321 ,  C23C28/34 ,  C23C28/347 ,  F01D5/084 ,  F01D9/06 ,  F01D25/18 ,  F05C2201/0463 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/509 ,  F05D2300/611 ,  F16L58/08 ,  F16L58/14

    Abstract: Cooling steam delivery tubes extend axially along the outer rim of a gas turbine rotor for supplying cooling steam to and returning spent cooling steam from the turbine buckets. Because of the high friction forces at the interface of the tubes and supporting elements due to rotor rotation, a low coefficient of friction coating is provided at the interface of the tubes and support elements. On each surface, a first coating of a cobalt-based alloy is sprayed onto the surface at high temperature. A portion of the first coating is machined off to provide a smooth, hard surface. A second ceramic-based solid film lubricant is sprayed onto the first coating. By reducing the resistance to axial displacement of the tubes relative to the supporting elements due to thermal expansion, the service life of the tubes is substantially extended.

    Abstract translation: 冷却蒸汽输送管沿着燃气涡轮机转子的外缘轴向延伸，用于将冷却蒸汽供给并从涡轮机叶返回废冷却蒸汽。 由于由于转子旋转而在管和支撑元件的界面处的高摩擦力，在管和支撑元件的界面处提供了低摩擦系数涂层。 在每个表面上，钴基合金的第一涂层在高温下喷涂到表面上。 第一涂层的一部分被加工以提供光滑的硬表面。 将第二陶瓷基固体膜润滑剂喷涂到第一涂层上。 通过由于热膨胀减小管相对于支撑元件的轴向位移的阻力，管的使用寿命显着延长。

    Steam turbine rotor shaft
    28.
    发明申请
    Steam turbine rotor shaft 有权
    蒸汽轮机转子轴

    公开(公告)号：US20010041137A1

    公开(公告)日：2001-11-15

    申请号：US09797989

    申请日：2001-03-05

    Inventor： Yutaka Fukui ,  Hiroyuki Doi ,  Masahiko Arai ,  Ryo Hiraga ,  Kenichiro Nomura ,  Toshio Fujita ,  Yasuhiko Tanaka

    IPC: F01D025/00

    CPC classification number: F01D5/28 ,  C21D8/0205 ,  C21D9/28 ,  C21D9/38 ,  C22C38/001 ,  C22C38/44 ,  C22C38/46 ,  C22C38/48 ,  C22C38/52 ,  C22C38/54 ,  F01D25/005 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/31 ,  F05D2240/60 ,  F05D2300/131 ,  F05D2300/132

    Abstract: The main object of the present invention is to provide a steam turbine rotor shaft whose high-temperature strength is excellent at a selected temperature of 650 degrees C. A steam turbine rotor shaft comprising 0.05% to 0.20% by weight of carbon, 0.20% or less by weight of silicon, 0.05% to 1.5% by weight of manganese, 0.01% to 1.0% by weight of nickel, 9.0% to 13.0% by weight of chrome, 0.05% to 2.0% by weight of molybdenum, 0.5% to 5.0% by weight of tungsten, 0.05% to 0.30% by weight of vanadium, 0.01% to 0.20% by weight of niobium, 0.5% to 10.0% by weight of cobalt, 0.01% to 0.1% by weight of nitrogen, 0.001% to 0.030% by weight of boron, 0.0005% to 0.006% by weight of aluminum, and the remaining parts substantially comprising iron and inevitable impurities.

    Abstract translation: 本发明的主要目的是提供一种在650℃的选定温度下其高温强度优异的汽轮机转子轴。包含0.05％至0.20％重量的碳，0.20％的蒸汽轮机转子轴 较少的硅，0.05〜1.5重量％的锰，0.01〜1.0重量％的镍，9.0〜13.0重量％的铬，0.05〜2.0重量％的钼，0.5〜5.0重量％ 钨，0.05〜0.30重量％的钒，0.01〜0.20重量％的铌，0.5〜10.0重量％的钴，0.01〜0.1重量％的氮，0.001〜0.030重量％ 重量百分比的硼，0.0005％至0.006％的铝，其余部分基本上包含铁和不可避免的杂质。

    Method of forming high-temperature components and components formed thereby
    29.
    发明授权
    Method of forming high-temperature components and components formed thereby 有权
    形成高温部件和由此形成的部件的方法

    公开(公告)号：US06168871A

    公开(公告)日：2001-01-02

    申请号：US09329625

    申请日：1999-06-10

    Applicant: Ann Melinda Ritter ,  Paul Leonard Dupree ,  Melvin Robert Jackson ,  Donald Norman Wemple, Jr.

    Inventor： Ann Melinda Ritter ,  Paul Leonard Dupree ,  Melvin Robert Jackson ,  Donald Norman Wemple, Jr.

    IPC: B22F702

    CPC classification number: F01D5/18 ,  B22F3/1208 ,  B22F5/04 ,  B22F7/062 ,  B22F2998/00 ,  B22F2998/10 ,  B23P15/04 ,  F01D5/28 ,  F01D5/282 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/20 ,  F05D2230/22 ,  F05D2300/603 ,  Y10T428/12028 ,  B22F1/0003 ,  B22F2207/01 ,  B22F3/15

    Abstract: A method for forming an exterior surface of a high-temperature component, such as a blade or vane of a gas turbine engine. The method entails forming a shell by a powder metallurgy technique that yields an airfoil whose composition can be readily tailored for the particular service conditions of the component. The method generally entails providing a pair of inner and outer mold members that form a cavity therebetween. One or more powders and any desired reinforcement material are then placed in the cavity and then consolidated at an elevated temperature and pressure in a non-oxidizing atmosphere. Thereafter, at least the outer mold member is removed to expose the consolidated powder structure. By appropriately shaping the mold members to tailor the shape of the cavity, the consolidated powder structure has the desired shape for the exterior shell of a component, such that subsequent processing of the component does not require substantially altering the configuration of the exterior shell. The airfoil can be produced as a free-standing article or produced directly on a mandrel that subsequently forms the interior structure of the component. In one embodiment, an airfoil is configured to have double walls through which cooling air flows.

    Abstract translation: 一种用于形成诸如燃气轮机的叶片或叶片的高温部件的外表面的方法。 该方法需要通过粉末冶金技术形成壳体，该技术产生的翼型件的组合可以容易地根据部件的特定使用条件进行定制。 该方法通常需要提供一对在其间形成空腔的内部和外部模具构件。 然后将一种或多种粉末和任何所需的增强材料置于空腔中，然后在非氧化性气氛中在升高的温度和压力下固化。 此后，至少移除外模构件以暴露固结的粉末结构。 通过适当地成型模具以适应空腔的形状，固结的粉末结构具有用于组件的外壳的期望的形状，使得组件的后续处理不需要基本上改变外壳的构造。 翼型件可以作为独立制品生产，或直接制造在随后形成部件的内部结构的心轴上。 在一个实施例中，翼型构造成具有双壁，冷却空气流过该壁。

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