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    Lubricating system for thermal medium delivery parts in a gas turbine
    61.
    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
    62.
    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
    63.
    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。

    가스 터빈내에서의 코팅, 튜브 및 시일 조립체
    66.
    发明公开
    가스 터빈내에서의 코팅, 튜브 및 시일 조립체 失效
    燃气涡轮加热部件润滑系统

    公开(公告)号：KR1020010020088A

    公开(公告)日：2001-03-15

    申请号：KR1019990044749

    申请日：1999-10-15

    Applicant: 제너럴 일렉트릭 캄파니

    Inventor： 마시토마스챨스

    IPC: F02C7/00 ,  F16J15/00 ,  B32B15/00 ,  B22F5/04

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

    Abstract: PURPOSE: A lubrication system for heat medium supply part of gas turbine is provided to improve abrasion resistance life of parts in touch with each other, by providing first membrane of cobalt alloy piled on one of the pipes and on surface of pipe support and second membrane put on top of the first membrane base material in case of cutting off of rotation balance adjustment part. CONSTITUTION: A membrane with low friction coefficient is provided on contact surface of pipe and supporting parts(79), for instance, of enlarged land part(76) and bush(79). The first membrane is applied to inner surface of enlarged land part(76) and bush(79) contacting the former. Since the first membrane is coupled with nickel alloy of enlarged land(76) and bush(79) substantially at molecular level, it is composed of high-density cobalt system alloy, sheathed by spraying onto the surface at high temperature. After applying this first membrane, a machine finish is made on the surface to get smoothness. For the second membrane, ceramic system lubricant is sprayed onto the first membrane, and baked for specified time at specified temperature, then for specified time at lower temperature.

    Abstract translation: 目的：提供一种用于燃气轮机的热介质供应部分的润滑系统，以提高彼此接触的部件的耐磨性寿命，通过提供堆焊在其中一个管道上的第一个钴合金膜和管支撑件和第二膜 在切断旋转平衡调节部件的情况下，放在第一膜基材的顶部。 构成：在管道和支撑部件（79）的接触表面上设置具有低摩擦系数的膜，例如扩大的陆部（76）和衬套（79）。 将第一膜施加到与前者接触的扩大陆部（76）和衬套（79）的内表面上。 由于第一个膜与大面积分散水平的大面积（76）和衬套（79）的镍合金结合，所以由高密度钴系合金组成，通过高温喷涂在表面上。 应用该第一膜后，在表面上进行机器加工以获得平滑度。 对于第二个膜，将陶瓷系统润滑剂喷涂到第一个膜上，并在规定温度下烘烤规定时间，然后在较低温度下规定的时间。

    HEAT SHIELD ELEMENT, GAS TURBINE
    67.
    发明申请
    HEAT SHIELD ELEMENT, GAS TURBINE 审中-公开
    热风元件，气体涡轮

    公开(公告)号：WO2013011126A2

    公开(公告)日：2013-01-24

    申请号：PCT/EP2012/064286

    申请日：2012-07-20

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SZIJARTO, Janos ,  GRANBERG, Per ,  UTRIAINEN, Esa

    Inventor： SZIJARTO, Janos ,  GRANBERG, Per ,  UTRIAINEN, Esa

    IPC: F01D11/08 ,  F01D25/14

    CPC classification number: F01D11/08 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2230/13 ,  F05D2230/22 ,  F05D2240/11 ,  F05D2250/185 ,  F05D2250/25 ,  F05D2260/221

    Abstract: The invention relates to a heat shield element (HS) for a gas turbine (GT) comprising an areal wall section (WS), which extends with regard to a central axis (CA) in an axial direction and a circumferential direction (CD), said wall section (WS) being defined by limiting edges of the heat shield element (HS), said wall section (WS) is of a defined thickness (TH), said thickness depending on the axial and circumferential position extending radially from an inner surface (IS) to an outer surface (OS) said inner surface (IS) is exposed to a hot gas path (HGP) and said outer surface (OS) is exposed to a coolant (CO) contained in a cavity (CV), wherein the heat shield element (HS) is provided with mounting elements (ME) suitable for mounting on a supporting structure (SP). To improve cooling efficiency it is proposed that cooling channels (CC) are provided through the wall of said wall section (WS) said cooling channels (CC) comprising a first section (S1) starting at the inner surface (IS), further comprising a second section (S2) extending between the inner surface (IS) and the outer surface (OS) along a length of at least three times the thickness (TH) of the wall section (WS) at that specific area of the second section and comprising a third section (S3) joining the hot gas path through the inner surface (IS) or through a limiting edge so that said cooling channels (CC) connect said cavity (CV) with the hot gas path (HGP).

    Abstract translation: 本发明涉及一种用于燃气轮机（GT）的隔热元件（HS），其包括相对于中心轴线（CA）在轴向和圆周方向（CD）上延伸的面壁部分（WS） 所述壁部分（WS）由所述隔热元件（HS）的限制边限定，所述壁部分（WS）具有限定的厚度（TH），所述厚度取决于从内表面径向延伸的轴向和周向位置 （IS）到外表面（OS），所述内表面（IS）暴露于热气路径（HGP），并且所述外表面（OS）暴露于包含在空腔（CV）中的冷却剂（CO），其中 隔热元件（HS）设置有适于安装在支撑结构（SP）上的安装元件（ME）。 为了提高冷却效率，提出通过所述壁部（WS）的壁提供冷却通道（CC），所述冷却通道（CC）包括从内表面（IS）开始的第一部分（S1），还包括 所述第二部分（S2）在所述第二部分的所述特定区域处沿所述壁部分（WS）的厚度（TH）的至少三倍的长度在所述内表面（IS）和所述外表面（OS）之间延伸，并且包括 第三部分（S3），其通过内表面（IS）或通过限制边缘接合热气路径，使得所述冷却通道（CC）将所述空腔（CV）与热气路径（HGP）连接。

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