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    Ring-shaped disk for gas turbine
    222.
    发明授权
    Ring-shaped disk for gas turbine 有权
    用于燃气轮机的环形盘

    公开(公告)号：US08187532B2

    公开(公告)日：2012-05-29

    申请号：US12991511

    申请日：2009-05-08

    Applicant: Jun Ohsone ,  Akira Mitsuhashi ,  Takanori Matsui ,  Yuji Ishiwari

    Inventor： Jun Ohsone ,  Akira Mitsuhashi ,  Takanori Matsui ,  Yuji Ishiwari

    IPC: C22C19/05

    CPC classification number: F01D5/02 ,  B21H1/06 ,  C22C19/056 ,  C22F1/10 ,  F01D5/28 ,  F05C2201/0466 ,  F05D2260/94 ,  F05D2300/121 ,  F05D2300/131 ,  F05D2300/132 ,  F05D2300/133

    Abstract: This ring-shaped disk for a gas turbine includes a ring-shaped disk material consisting of a Ni-based alloy, wherein the Ni-based alloy has a composition that includes, in terms of percent by mass, Ni: 50.00 to 55.00%, Cr: 17.0 to 21.0%, Nb: 4.75 to 5.60%, Mo: 2.8 to 3.3%, Ti: 0.65 to 1.15%, Al: 0.20 to 0.80%, and C: 0.01 to 0.08%, with the balance being Fe and inevitable impurities, and has a microstructure in which δ phase particles are distributed in a matrix thereof, and wherein, in the microstructure, flattened δ phase particles of which maximum length directions are oriented at angles within a range of 60 to 120° with respect to a radial direction of the ring-shaped disk material are present in an amount of 60% or more of a total amount of the δ phase particles distributed in the matrix.

    Abstract translation: 该用于燃气轮机的环形盘包括由Ni基合金构成的环形盘材料，其中Ni基合金的组成按质量百分比计包含Ni：50.00至55.00％， Cr：17.0〜21.0％，Nb：4.75〜5.60％，Mo：2.8〜3.3％，Ti：0.65〜1.15％，Al：0.20〜0.80％，C：0.01〜0.08％ 杂质，并且具有其中δ相颗粒分布在其基体中的微结构，并且其中在微观结构中，最大长度方向相对于a的角度在60至120°的范围内的平坦化的δ相颗粒 环状盘材的径向方向以分散在基体中的δ相粒子总量的60％以上的量存在。

    TURBINE ENGINE ALLOYS AND CRYSTALLINE ORIENTATIONS
    227.
    发明申请
    TURBINE ENGINE ALLOYS AND CRYSTALLINE ORIENTATIONS 有权
    涡轮发动机合金和结晶方位

    公开(公告)号：US20110081235A1

    公开(公告)日：2011-04-07

    申请号：US11486743

    申请日：2006-07-13

    Applicant: Dilip M. Shah ,  Joseph G. Hillebrand ,  Daniel E. Kane

    Inventor： Dilip M. Shah ,  Joseph G. Hillebrand ,  Daniel E. Kane

    IPC: F01D11/00 ,  B23P15/04

    CPC classification number: F01D11/005 ,  F01D5/16 ,  F01D5/22 ,  F01D5/24 ,  F01D11/006 ,  F01D17/04 ,  F01D25/06 ,  F02C7/052 ,  F05C2201/0466 ,  F05D2300/11 ,  F05D2300/50 ,  F05D2300/607 ,  F16J15/0806 ,  F16J15/0887 ,  G01H11/08 ,  G10K11/24 ,  Y10T29/4932

    Abstract: A method is provided for engineering a single crystal cast gas turbine engine first component for cooperating with a second component. An at least local first operational stress on the first component is determined. The first operational stress has a first direction. A crystal orientation within the component or a physical configuration of the component is selected so that the first operational stress produces a desired engagement of the first component with the second component associated with either a negative Poisson's effect or high Poisson's effect in a second direction. Single crystal or highly textured iron- and nickel-base alloys enable one to use such effect in high temperature and/or corrosive environments.

    Abstract translation: 提供了一种用于工程化单晶铸造燃气涡轮发动机第一部件以与第二部件配合的方法。 确定第一部件上的至少局部第一操作应力。 第一个操作压力有第一个方向。 选择部件内的晶体取向或部件的物理结构，使得第一操作应力产生第一部件与第二部件的期望接合，该第二部件与第二方向上的负泊松效应或高泊松效应相关联。 单晶或高度纹理化的铁和镍基合金使得能够在高温和/或腐蚀性环境中使用这种效果。

    STEAM TURBINE FACILITY
    228.
    发明申请
    STEAM TURBINE FACILITY 审中-公开
    蒸汽涡轮机设施

    公开(公告)号：US20110030374A1

    公开(公告)日：2011-02-10

    申请号：US12674073

    申请日：2009-07-30

    Applicant: Shin Nishimoto ,  Yoshinori Tanaka ,  Tatsuaki Fujikawa ,  Ryuichi Yamamoto

    Inventor： Shin Nishimoto ,  Yoshinori Tanaka ,  Tatsuaki Fujikawa ,  Ryuichi Yamamoto

    IPC: F01K23/16

    CPC classification number: F01D5/063 ,  F01D13/003 ,  F01D13/02 ,  F01D25/24 ,  F01K7/22 ,  F05C2201/0466 ,  F05D2220/31

    Abstract: Provided is a steam turbine facility capable of suppressing the possibility of vibration occurrence and a drastic increase in facility cost, thereby realizing an increase in size of the facility, even if steam conditions of 650° C. or higher are adopted. In a steam turbine facility including a high-pressure turbine, an intermediate-pressure turbine, and a low-pressure turbine, the high-pressure turbine is separated into a first high-pressure turbine part on a high-temperature and high-pressure side and a second high-pressure turbine part on a low-temperature and low-pressure side, the intermediate-pressure turbine is separated into a first intermediate-pressure turbine part on the high-temperature and high-pressure side and a second intermediate-pressure turbine part on the low-temperature and low-temperature side, the first high-pressure turbine part and the first intermediate-pressure turbine part are integrated to form a first integrated part, the second high-pressure turbine part and the second intermediate-pressure turbine part are integrated to form a second integrated part, at least any one of the rotors and casings of the turbines into which steam with a temperature of 650° C. or higher is introduced are constructed by joining together a plurality of members formed from Ni-based alloy through welding as a whole.

    Abstract translation: 提供一种能够抑制振动发生的可能性和设备成本急剧增加的汽轮机设备，即使采用650℃以上的蒸汽条件，也能够实现设备尺寸的增加。 在包括高压涡轮机，中压涡轮机和低压涡轮机的蒸汽轮机设备中，高压涡轮机被分离成高温高压侧的第一高压涡轮机部件 以及低温低压侧的第二高压涡轮机部，将中压涡轮机分离成高温侧和高压侧的第一中压涡轮部，第二中压 涡轮机部分在低温低温侧，第一高压涡轮机部分和第一中压涡轮部分被一体化以形成第一集成部分，第二高压涡轮部分和第二中压 涡轮部分被一体化以形成第二集成部件，引入涡轮的转子和壳体中的至少任一个，其中引入了650℃或更高的温度的蒸汽，通过连接 通过焊接整体由Ni基合金形成的多个部件组合在一起。

    METHOD OF REPAIRING RUN-IN COATINGS
    229.
    发明申请
    METHOD OF REPAIRING RUN-IN COATINGS 有权
    修复运行涂层的方法

    公开(公告)号：US20100330271A1

    公开(公告)日：2010-12-30

    申请号：US12308523

    申请日：2007-06-14

    Applicant: Manfred A. Daeubler ,  Andre Werner ,  Heinrich Walter

    Inventor： Manfred A. Daeubler ,  Andre Werner ,  Heinrich Walter

    IPC: B05D3/02

    CPC classification number: F01D11/12 ,  B23P6/007 ,  C23C10/16 ,  C23C10/18 ,  C23C26/00 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/762 ,  F05D2230/10 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2230/40 ,  F05D2230/80 ,  F05D2300/11 ,  F05D2300/224 ,  F05D2300/228

    Abstract: The present invention relates to a method of repairing intake coatings (12), in particular intake coatings for use in compressor and turbine components, wherein the process comprises the following steps: a) filling of a damaged place (10) of the inlet coating (12) with a material (18) whose material composition corresponds to that of the intake coating (12) or is comparable to this or whose materials properties are comparable to the materials properties of the intake coating (12); b) drying of the material (18) introduced into the damaged place (10); c) application of a diffusion donor layer (20) over the region of the damaged place (10) and onto the introduced material (18); and d) heat treatment of the intake coating (12) at least in the region of the damaged place (10) to effect local diffusion of at least one metallic element from the diffusion donor layer (20) into the introduced material (18).

    Abstract translation: 本发明涉及一种修复进口涂层（12）的方法，特别是用于压缩机和涡轮机部件的进料涂层，其中该方法包括以下步骤：a）填充入口涂层的损坏场所（10）（ 12）与其材料成分对应于进料涂层（12）的材料（18）或与其相当或其材料性质与进料涂层（12）的材料性质相当的材料（18）; b）干燥引入损坏场所（10）的材料（18）; c）在损坏的地方（10）的区域上施加扩散施主层（20）并且到引入的材料（18）上; 以及d）至少在损坏处（10）的区域中对进气涂层（12）进行热处理，以使至少一种金属元素从扩散施主层（20）局部扩散到引入材料（18）中。

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