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    Thermal barrier coating for industrial gas turbine blade, and Industrial gas turbine using the same
    3.
    发明公开
    Thermal barrier coating for industrial gas turbine blade, and Industrial gas turbine using the same 审中-公开
    Gasturbinenschaufel工业公司和工业公司Gurburbine damit

    公开(公告)号：EP2684976A2

    公开(公告)日：2014-01-15

    申请号：EP13175928.4

    申请日：2013-07-10

    申请人： Hitachi Ltd. ,  National University Corporation Hokkaido University

    发明人： Izumi, Takeshi ,  Arikawa, Hideyuki ,  Kojima, Yoshitaka ,  Mebata, Akira ,  Kasuya, Tadashi ,  Narita, Toshio

    IPC分类号： C23C10/00 ,  C23C28/00

    CPC分类号： F01D5/288 ,  C23C10/00 ,  C23C10/02 ,  C23C10/38 ,  C23C10/60 ,  C23C28/00 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/3455 ,  C23C28/42 ,  F05D2300/10 ,  Y02T50/672 ,  Y10T428/12618

    摘要： Disclosed is a turbine blade for an industrial gas turbine including a blade substrate; a multilayer alloy coating containing a diffusion barrier layer; a bond coat; and a top coat, the blade substrate being formed of a single crystal alloy which consists essentially of 0.06 to 0.08% of C, 0.016 to 0.035% of B, 0.2 to 0.3% of Hf, 6.9 to 7.3% of Cr, 0.7 to 1.0% of Mo, 7.0 to 9.0% of W, 1.2 to 1.6% of Re, 8.5 to 9.5% of Ta, 0.6 to 1.0% of Nb, 4.9 to 5.2% of Al, 0.8 to 1.2% of Co, and the balance being Ni and incidental impurities by weight, the multilayer alloy coating, the bond coat and the top coat being directly and sequentially laminated on a surface of the blade substrate, in which the diffusion barrier layer is a multilayer and a discontinuous layer. Thus, the thermal barrier coating structure including a diffusion barrier layer can be provided for the single-crystal turbine blade for the industrial gas turbine formed of a single crystal alloy. The thermal barrier coating structure can suppress growth of a secondary reaction zone caused by element diffusion into the substrate, and can provide durability against thermal fatigue due to thermal cycles and durability against mechanical fatigue.

    摘要翻译： 公开了一种用于工业燃气轮机的涡轮叶片，其包括叶片基板; 含有扩散阻挡层的多层合金涂层; 粘合外套; 和顶涂层，所述刀片基材由单晶合金形成，所述单晶合金基本上由C：0.06〜0.08％，B：0.016〜0.035％，Hf：0.2〜0.3％，Cr：6.9〜7.3％，0.7〜1.0 Mo为7.0〜9.0％，Re为1.2〜1.6％，Ta为8.5〜9.5％，Nb为0.6〜1.0％，Al为4.9〜5.2％，Co为0.8〜1.2％，余量为 Ni和重量杂质，多层合金涂层，粘结涂层和顶涂层直接依次层压在其中扩散阻挡层为多层和不连续层的叶片基板的表面上。 因此，对于由单晶合金形成的工业燃气轮机的单晶涡轮叶片，能够提供包括扩散阻挡层的热障涂覆结构。 热障涂层结构可以抑制由元件扩散到基板中引起的二次反应区的生长，并且可以提供耐热循环和对机械疲劳的耐久性的热疲劳的耐久性。

    Turbine blade for industrial gas turbine and industrial gas turbine
    4.
    发明公开
    Turbine blade for industrial gas turbine and industrial gas turbine 审中-公开
    工业工业和工业汽车工程学院

    公开(公告)号：EP2690197A1

    公开(公告)日：2014-01-29

    申请号：EP13169377.2

    申请日：2013-05-27

    申请人： Hitachi Ltd. ,  National University Corporation Hokkaido University

    发明人： Izumi, Takeshi ,  Arikawa, Hideyuki ,  Kojima, Yoshitaka ,  Mebata, Akira ,  Kasuya, Tadashi ,  Narita, Toshio

    IPC分类号： C23C28/00 ,  F01D5/28

    CPC分类号： F01D5/288 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  C23C28/347

    摘要： A turbine blade for industrial gas turbine is used which includes a blade substrate formed of a single-crystal heat-resistant alloy containing C: 0.06 to 0.08%, B: 0.016 to 0.035%, Hf: 0.2 to 0.3%, Cr: 6.9 to 7.3%, Mo: 0.7 to 1.0%, W: 7.0 to 9.0%, Re: 1.2 to 1.6%, Ta: 8.5 to 9.5%, Nb: 0.6 to 1.0%, Al: 4.9 to 5.2%, Co: 0.8 to 1.2%, and the remainder substantially consisting of Ni with reference to mass, and includes a diffusion barrier layer, a metal layer, a bond coat, and a top coat, these layers and coats being stacked in this order on a surface of the blade substrate, the metal layer having a thickness of 5 to 30 µm. Thus, the turbine blade can be provided which has a thermal barrier coating formed without loss of a function of the diffusion barrier layer.

    摘要翻译： 使用工业燃气轮机的涡轮叶片，其包括由C：0.06〜0.08％，B：0.016〜0.035％，Hf：0.2〜0.3％，Cr：6.9〜 7.3％，Mo：0.7〜1.0％，W：7.0〜9.0％，Re：1.2〜1.6％，Ta：8.5〜9.5％，Nb：0.6〜1.0％，Al：4.9〜5.2％，Co：0.8〜1.2 ％，余量基本上由质量的Ni组成，并且包括扩散阻挡层，金属层，粘合涂层和顶涂层，这些层和涂层依次层叠在刮板基板的表面上 ，金属层的厚度为5〜30μm。 因此，可以提供涡轮叶片，其具有在不丧失扩散阻挡层的功能的情况下形成的热障涂层。

    Gas turbine with honeycomb seal
    9.
    发明公开
    Gas turbine with honeycomb seal 审中-公开
    Gasturbine mit Wabendichtung

    公开(公告)号：EP2813671A1

    公开(公告)日：2014-12-17

    申请号：EP14170172.2

    申请日：2014-05-28

    申请人： Mitsubishi Hitachi Power Systems, Ltd.

    发明人： Arikawa, Hideyuki ,  Kasuya, Tadashi ,  Kojima, Yoshitaka ,  Watanabe, Yasuyuki ,  Murakata, Tadashi ,  Ichikawa, Kunihiro ,  Konrai, Takumi

    IPC分类号： F01D11/12

    CPC分类号： F01D11/127 ,  F05D2250/283

    摘要： A gas turbine 100 includes a compressor 10, a combustor 20, and a turbine 30 with a honeycomb seal 7 disposed so as to be secured to a casing side in a clearance between the casing 1 and turbine blades 5A-5C rotating around a rotating shaft 4 extending in a longitudinal direction of the casing 1 and a seal fin 6 provided on an end face of each of the turbine blades 5A - 5C facing the honeycomb seal 7, the seal fin 6 extending in a direction perpendicular to the rotating shaft 4. The honeycomb seal 7 is formed by a plurality of corrugated thin metal sheets 71 overlapped with each other at walls of node 71a thereof and the walls of node 71 brazed with each other, each of the corrugated thin metal sheets 71 having trapezoids alternately continued. A longer direction (Y1 direction) of the wall of node 71a of the honeycomb seal 7 is tilted with respect to the rotational direction (Z direction) of the turbine blades 5A - 5C.

    摘要翻译： 燃气轮机100包括压缩机10，燃烧器20和具有蜂窝密封件7的涡轮机30，蜂窝密封件7被设置成在壳体1和围绕旋转轴线旋转的涡轮机叶片5A-5C之间的间隙中固定到壳体侧 4和设置在面对蜂窝密封件7的涡轮机叶片5A-5C的端面上的密封翅片6，密封翅片6沿垂直于旋转轴4的方向延伸。 蜂窝状密封件7由在其节点71a的壁处彼此重叠的多个波纹状薄金属片71和彼此钎焊的节点71的壁形成，每个具有梯形的波纹状薄金属片71交替连续。 蜂窝密封件7的节点71a的壁的长方向（Y1方向）相对于涡轮叶片5A-5C的旋转方向（Z方向）倾斜。