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23 条记录 (耗时 0.012 秒)

    Gas turbine shroud with ceramic abradable coatings
    3.
    发明公开
    Gas turbine shroud with ceramic abradable coatings 有权
    GASTURBINENUMMANTELUNG MIT ABREIBBAREN KERAMISCHEN BESCHICHTUNGEN

    公开(公告)号：EP2354276A1

    公开(公告)日：2011-08-10

    申请号：EP11151974.0

    申请日：2011-01-25

    申请人： Hitachi Ltd.

    发明人： Kojima, Yoshitaka ,  Arikawa, Hideyuki ,  Mebata, Akira ,  Kasuya, Tadashi ,  Doi, Hiroyuki ,  Ichikawa, Kunihiro

    IPC分类号： C23C28/00 ,  F01D11/08

    CPC分类号： C23C28/00 ,  F01D11/122 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2250/181 ,  F05D2300/21

    摘要： There is provided a gas turbine shroud including a ceramic abradable coating used as a gap adjusting component that can reduce a fluid leakage from a gap and increase turbine efficiency. A gas turbine ceramic abradable coating includes a bond layer (2), a thermal barrier ceramic layer (3), and a porous ceramic abradable layer (4) (hardness may be RC15Y: 80±3). A slit groove (5) is provided in the porous ceramic abradable layer (4) by machining. A width of a rectangular section of the ceramic abradable layer (4) divided by the slit groove (5) may be set to a range of 2 to 7 mm.

    摘要翻译： 提供了一种燃气轮机罩，其包括用作间隙调节部件的陶瓷耐磨涂层，其可以减少从间隙泄漏的液体并提高涡轮机效率。 燃气轮机陶瓷耐磨涂层包括粘合层（2），热障陶瓷层（3）和多孔陶瓷耐磨层（4）（硬度可以是RC15Y：80±3）。 通过机加工在多孔陶瓷耐磨层（4）中设置狭槽（5）。 由狭缝槽（5）分割的陶瓷耐磨层（4）的矩形截面的宽度可以设定在2〜7mm的范围内。

    Turbine blade for industrial gas turbine and industrial gas turbine
    8.
    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。

    Method of working a cooling hole of a turbine blade
    10.
    发明公开
    Method of working a cooling hole of a turbine blade 有权
    Verfahren zur Herstellung einesKühllochseiner Turbinenschaufel

    公开(公告)号：EP2439377A2

    公开(公告)日：2012-04-11

    申请号：EP11184159.9

    申请日：2011-10-06

    申请人： Hitachi, Ltd.

    发明人： Arikawa, Hideyuki ,  Mebata, Akira ,  Kojima, Yoshitaka ,  Ichikawa, Kunihiro ,  Izumi, Takeshi

    IPC分类号： F01D5/28

    CPC分类号： F01D5/288 ,  C23C4/02 ,  C23C4/134 ,  C23C4/18 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/186 ,  F05D2230/12 ,  F05D2230/80 ,  F05D2230/90 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T29/49341

    摘要： Method of working cooling hole of turbine blade
    In a turbine blade having a TBC and a very lot of film cooling holes, the invention provides a method of executing the TBC in the turbine blade without any occlusion of the film cooling hole in accordance with a simple method. In a method of working a film cooling hole (4, 27) which communicates with an internal cooling passage of a turbine blade from an outer surface, in the turbine blade which has a heat shield coating (3) and the internal cooling passage, there is employed a method of working a cooling hole of a turbine including (1) a step of executing a bond coat (2) on a blade base material (1), (2) a step of piercing a cooling hole (4, 27) in accordance with an electric discharge machining, (3) a step of executing a top coat (3), and (4) a step of removing the top coat in accordance with a mechanical method with respect to a band-like region including a row of cooling holes, by using an abrasive blasting, a water jet method or the like. Accordingly, an occlusion of the cooling hole, and a damage of the TBC due to the piercing are hardly generated, and it is possible to more simply work the blade which uses the film cooling system having a higher reliability and the TBC together.

    摘要翻译： 涡轮叶片工作冷却孔的方法在具有TBC和非常多的薄膜冷却孔的涡轮机叶片中，本发明提供一种在涡轮叶片中执行TBC的方法，而不会根据简单的方式遮盖薄膜冷却孔 方法。 在从外表面与涡轮叶片的内部冷却通道连通的薄膜冷却孔（4,27）的工作方法中，在具有隔热涂层（3）和内部冷却通道的涡轮机叶片中， 采用了一种对涡轮机的冷却孔进行加工的方法，包括：（1）在叶片基材（1）上进行粘合涂层（2）的步骤，（2）穿过冷却孔（4,27）的步骤， 根据放电加工，（3）执行面涂层（3）的步骤，以及（4）根据机械方法相对于包括行的带状区域去除面涂层的步骤 的冷却孔，通过使用喷砂法，喷水法等。 因此，几乎不产生冷却孔的堵塞和由于穿孔引起的TBC的损坏，并且可以更简单地将使用具有较高可靠性的薄膜冷却系统的刀片和TBC一起工作。