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23 条记录 (耗时 0.013 秒)

    Gas turbine blade and manufacturing method thereof
    1.
    发明授权
    Gas turbine blade and manufacturing method thereof 有权
    燃气轮机叶片及其制造方法

    公开(公告)号：US08813361B2

    公开(公告)日：2014-08-26

    申请号：US13211417

    申请日：2011-08-17

    申请人： Shinya Imano ,  Kunihiro Ichikawa ,  Hiroyuki Doi ,  Katsumi Tanaka

    发明人： Shinya Imano ,  Kunihiro Ichikawa ,  Hiroyuki Doi ,  Katsumi Tanaka

    IPC分类号： B21D53/78

    CPC分类号： C22C19/051 ,  C22C19/05 ,  F01D5/005 ,  F05D2230/235 ,  F05D2230/80

    摘要： In a gas turbine blade where a part of the γ′ phase precipitation strengthened type Ni-based alloy base material is composed of a weld metal, the weld metal is a Ni-based alloy containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt. %, Co from 12 to 17 wt. %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. %, and Al of 1 wt. % or less, in which the oxygen content is 0 to 30 ppm, the Ti content from 0 to 0.1 wt. %, and the Re content from 0 to 0.5 wt. %. A blade base metal is manufactured by the step of stripping, the step of solution heat treatment where the γ′ phase is dissolved again, the step of welding in an inert gas chamber by a TIG method using a welding wire where the weld metal can be obtained, the step of HIP treatment at 1100° C. to 1150° C., and the step of an aging treatment at 835° C. to 855° C.

    摘要翻译： 在γ相析出强化型Ni基合金基材的一部分由焊接金属构成的燃气轮机叶片中，焊接金属为含有4.8〜5.3重量％的Ta的Ni系合金。 ％，Cr为18〜23wt。 ％，Co为12〜17wt。 ％，W为14〜18wt。 ％，C为0.03〜0.1wt。 ％，Mo为1〜2wt。 ％，Al为1重量％。 ％以下，氧含量为0〜30ppm，Ti含量为0〜0.1重量％。 ％，Re含量为0〜0.5wt。 ％。 通过剥离步骤，再次溶解γ'相的固溶热处理步骤，通过TIG法使用焊丝在焊接金属可以焊接的焊丝的惰性气体室中进行焊接的工序来制造刀片母材 在1100℃至1150℃下进行HIP处理的步骤，以及在835℃至855℃的时效处理步骤。

    High-temperature resistant component and gas turbine hot part
    2.
    发明授权
    High-temperature resistant component and gas turbine hot part 有权
    耐高温部件和燃气轮机热部件

    公开(公告)号：US08460799B2

    公开(公告)日：2013-06-11

    申请号：US12822208

    申请日：2010-06-24

    申请人： Hideyuki Arikawa ,  Akira Mebata ,  Yoshitaka Kojima ,  Kunihiro Ichikawa ,  Hiroshi Haruyama

    发明人： Hideyuki Arikawa ,  Akira Mebata ,  Yoshitaka Kojima ,  Kunihiro Ichikawa ,  Hiroshi Haruyama

    IPC分类号： B32B15/00 ,  B32B15/04

    CPC分类号： F01D5/284 ,  C23C24/00 ,  C23C24/08 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  F05D2230/90 ,  F05D2260/95 ,  F05D2300/134 ,  F05D2300/21 ,  Y02T50/67 ,  Y02T50/671 ,  Y10T428/12479 ,  Y10T428/12597 ,  Y10T428/12611

    摘要： A high-temperature resistant component for, e.g., a gas turbine hot part, includes an alloy substrate containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer made of ceramic and an environmental barrier layer with corrosion resistance. An impregnated layer is provided between the environmental barrier layer and the thermal barrier layer. In the impregnated layer, the thermal barrier layer is impregnated with a part of the environmental barrier layer. The thermal barrier layer is made of a porous zirconia layer, and the environmental barrier layer includes silica as the principal component. The porous zirconia layer has pores impregnated with the part of the environmental barrier layer. As a result, the high-temperature resistant component has excellent corrosion resistance and excellent heat resistance.

    摘要翻译： 用于例如燃气轮机热部件的耐高温部件包括以Ni，Co或Fe为主要成分的合金基材，以及通过粘结涂层形成在基材的表面上的热障涂层。 热障涂层包括由陶瓷制成的多孔热障层和具有耐腐蚀性的环境阻挡层。 浸渍层设置在环境阻挡层和热障层之间。 在浸渍层中，热障层浸渍有环境阻挡层的一部分。 隔热层由多孔氧化锆层构成，环境阻挡层包含二氧化硅作为主要成分。 多孔氧化锆层具有浸渍有环境阻挡层的一部分的孔。 结果，耐高温组分具有优异的耐腐蚀性和优异的耐热性。

    Service life management system for high-temperature part of gas turbine
    5.
    发明授权
    Service life management system for high-temperature part of gas turbine 有权
    燃气轮机高温部分使用寿命管理系统

    公开(公告)号：US06636813B1

    公开(公告)日：2003-10-21

    申请号：US09913957

    申请日：2001-11-15

    申请人： Nobuhiro Isobe ,  Yasushi Hayasaka ,  Shigeo Sakurai ,  Kunihiro Ichikawa

    发明人： Nobuhiro Isobe ,  Yasushi Hayasaka ,  Shigeo Sakurai ,  Kunihiro Ichikawa

    IPC分类号： F01D902

    CPC分类号： G06Q10/06 ,  F01D21/003 ,  F02C9/00 ,  G05B23/0283

    摘要： A life management system for high-temperature parts of a gas turbine has one server system 3 and a plurality of client systems 5a, 5b, 5c, and 5d, all of which are connected via an Intranet. Further, the server system 3 manages a program for performing evaluation of the remaining life and the life management, and each of the client systems 5a, 5b, 5c, and 5d has a subprogram for accessing the database 4 and for entering data respectively. The clients are dedicated to different objects and share respective element data such as real component damage, design, materials, etc. which are necessary for the evaluation of the remaining life. Further, this system enables the operation of the gas turbine to be optimized based on the damage of the evaluated parts, hence contributing to operational cost reduction of the gas turbine.

    摘要翻译： 燃气轮机的高温部件的生命管理系统具有一个服务器系统3和多个客户端系统5a，5b，5c和5d，所有客户端系统都通过内联网连接。 此外，服务器系统3管理用于执行剩余寿命和寿命管理的评估的程序，并且每个客户端系统5a，5b，5c和5d具有用于访问数据库4并分别输入数据的子程序。 客户专用于不同的对象，并分享对剩余寿命进行评估所需的各个元素数据，例如实际元件损坏，设计，材料等。 此外，该系统能够基于评估部件的损坏来优化燃气轮机的运行，从而有助于燃气轮机的运行成本降低。

    Gas turbine combustor and gas turbine
    6.
    发明授权
    Gas turbine combustor and gas turbine 失效
    燃气轮机燃气轮机和燃气轮机

    公开(公告)号：US5630320A

    公开(公告)日：1997-05-20

    申请号：US357187

    申请日：1994-12-13

    申请人： Noriaki Matsuda ,  Kunihiro Ichikawa ,  Shigeru Azuhata ,  Nobuyuki Iizuka ,  Yoshikazu Moritomo ,  Yoshiharu Nakayama ,  Nariyoshi Kobayashi

    发明人： Noriaki Matsuda ,  Kunihiro Ichikawa ,  Shigeru Azuhata ,  Nobuyuki Iizuka ,  Yoshikazu Moritomo ,  Yoshiharu Nakayama ,  Nariyoshi Kobayashi

    IPC分类号： F23R3/18 ,  F23R3/30 ,  F23R3/34 ,  F02C1/02

    CPC分类号： F23R3/346 ,  F23R3/18

    摘要： A gas turbine combustor is provides with a stabilizer at a downstream side of a premixing device for premixing and supplying fuel and air into a combustion chamber. The stabilizer has a cylindrical part extending axially from an upstream end thereof to a downstream end and a stabilizing part at the downstream end of the cylindrical part for stabilizing a flame, and the stabilizer is mounted on an inside of the combustor by a plurality of members arranged annularly and secured to the inside of the combustor at their ends, each of the members having a part slidably inserted in an opening of the cylindrical part so as to restrict the stabilizer to move axially while allowing deformation of the stabilizer and another part supporting the upstream end of the cylindrical part so as to restrict radial movement of the stabilizer.

    摘要翻译： 燃气轮机燃烧器在预混合装置的下游侧设置有稳定器，用于将燃料和空气预混和供应到燃烧室中。 稳定器具有从其上游端向下游端轴向延伸的圆柱形部分和用于稳定火焰的圆柱形部分的下游端的稳定部分，并且稳定器通过多个部件安装在燃烧器的内部 环形地安装并固定在燃烧器的内部，每个构件具有可滑动地插入圆柱形部分的开口中的部分，以便限制稳定器轴向移动，同时允许稳定器变形，另一部分支撑 圆柱形部分的上游端，以限制稳定器的径向移动。

    GAS TURBINE COMPONENT HAVING THERMAL BARRIER COATING AND A GAS TURBINE USING THE COMPONENT
    7.
    发明申请
    GAS TURBINE COMPONENT HAVING THERMAL BARRIER COATING AND A GAS TURBINE USING THE COMPONENT 审中-公开
    具有热障涂层的气体涡轮机组件和使用组件的气体涡轮机

    公开(公告)号：US20120159952A1

    公开(公告)日：2012-06-28

    申请号：US13332605

    申请日：2011-12-21

    申请人： Hideyuki ARIKAWA ,  Akira Mebata ,  Yoshitaka Kojima ,  Kunihiro Ichikawa ,  Hiroshi Haruyama

    发明人： Hideyuki ARIKAWA ,  Akira Mebata ,  Yoshitaka Kojima ,  Kunihiro Ichikawa ,  Hiroshi Haruyama

    IPC分类号： F01D25/08 ,  F23R3/00 ,  F01D5/18

    CPC分类号： C23C28/04 ,  C23C28/042 ,  C23C28/046 ,  C23C28/048 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/6765

    摘要： The present invention provides gas turbine components having durability and reliability for use in a corrosive environment such as a turbine employing a low grade fuel, and also provides a gas turbine equipped with the components. One of the components is a gas turbine bucket/nozzle comprising a substrate made from an alloy containing Ni, Co, or Fe, a bonding layer made from an alloy and disposed over the substrate, and a thermal barrier coating disposed over the bonding layer. The thermal barrier coating includes a thermal barrier layer of porous ceramics, an environmental barrier layer containing silica, and an impregnation layer having a silica-containing material in the pores of the porous ceramics.

    摘要翻译： 本发明提供了具有耐久性和可靠性的燃气轮机部件，其用于诸如使用低等级燃料的涡轮机等腐蚀性环境，并且还提供了配备有部件的燃气轮机。 其中一个部件是包括由含有Ni，Co或Fe的合金制成的基体的燃气涡轮机桶/喷嘴，由合金制成并设置在基板上的粘合层，以及设置在接合层上的热障涂层。 隔热涂层包括多孔陶瓷的阻热层，含有二氧化硅的环境阻挡层和在多孔陶瓷的孔中具有含二氧化硅的材料的浸渍层。

    METHOD OF WORKING COOLING HOLE OF TURBINE BLADE
    8.
    发明申请
    METHOD OF WORKING COOLING HOLE OF TURBINE BLADE 审中-公开
    涡轮叶片工作冷却孔的方法

    公开(公告)号：US20120084981A1

    公开(公告)日：2012-04-12

    申请号：US13253164

    申请日：2011-10-05

    申请人： Hideyuki Arikawa ,  Akira Mebata ,  Yoshitaka Kojima ,  Kunihiro Ichikawa ,  Takeshi Izumi

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

    IPC分类号： B23P15/02

    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 ,  Y02T50/6765 ,  Y10T29/49341

    摘要： In a method of working a film cooling hole 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 and the internal cooling passage, there is employed a method of working a cooling hole of a turbine including a step of executing a bond coat on a blade base material a step of piercing a cooling hole in accordance with an electric discharge machining, a step of executing a top coat, and 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.

    摘要翻译： 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的工作方法中，在具有隔热涂层和内部冷却通路的涡轮叶片中，采用了一种冷却 包括在叶片基材上执行粘合涂层的步骤，根据放电加工刺穿冷却孔的步骤，执行顶涂层的步骤，以及根据所述顶涂层的去除步骤 通过使用喷砂法，水喷射法等，相对于包括一排冷却孔的带状区域的机械方法。 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。