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    Quasicrystalline alloys and their use as coatings
    1.
    发明授权
    Quasicrystalline alloys and their use as coatings 失效
    准晶合金及其用作涂层

    公开(公告)号：US07060239B2

    公开(公告)日：2006-06-13

    申请号：US10401696

    申请日：2003-03-31

    申请人： Valery Shklover ,  Maxim Konter ,  Anton Kaiser ,  Kenneth Franklin Kelton

    发明人： Valery Shklover ,  Maxim Konter ,  Anton Kaiser ,  Kenneth Franklin Kelton

    IPC分类号： C22C14/00

    CPC分类号： C23C4/06 ,  C22F1/183 ,  C23C28/00 ,  C23C30/00

    摘要： The present invention relates to an icosahedral, quasicrystalline compound or compound present in the form of an approximant having the nominal composition: TivCrwAlxSiyOz, in which v=60-65; w=25-30; x=0-6; Y=8-15; z=8-20; and in which the atom percent of oxygen is in the range of between 8 and 15%, and that of aluminum in the range of between 2 to 5%. Due to their layered structure and ceramic intermediate layers, compounds of this type exhibit excellent properties, in particular for use as coatings for gas turbine components, such as for example, rotor blades or guide vanes.

    摘要翻译： 本发明涉及以具有标称组成的近似物形式存在的二十面体，准晶体化合物或化合物：Ti 其中v = 60-65;其中v = 60-65; w = 25-30; x = 0-6; Y = 8-15; z = 8-20; 并且其中氧的原子百分比在8至15％的范围内，铝的原子百分比在2至5％的范围内。 由于它们的层状结构和陶瓷中间层，这种类型的化合物表现出优异的性能，特别是用作燃气轮机部件（例如转子叶片或导向叶片）的涂层。

    FLUID FLOW MACHINE
    2.
    发明申请
    FLUID FLOW MACHINE 有权
    流体流化床

    公开(公告)号：US20100111683A1

    公开(公告)日：2010-05-06

    申请号：US12605405

    申请日：2009-10-26

    申请人： Maxim Konter ,  Sergey Vorontsov ,  Alexander Khanin ,  Alexey Karelin ,  Alexander Bone

    发明人： Maxim Konter ,  Sergey Vorontsov ,  Alexander Khanin ,  Alexey Karelin ,  Alexander Bone

    IPC分类号： F01D9/04

    CPC分类号： F01D5/142 ,  F01D9/041 ,  F05D2200/20 ,  F05D2240/301 ,  Y02T50/673

    摘要： A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1). To reduce the load on the rotor blades (8), the guide vanes (6) and the rotor blades (8) are coordinated at least in one stage (10) so that in a reference relative position between the respective guide vane (6) and the respective rotor blade (8), there is an axial distance (B) and a circumferential distance (C) between the outgoing flow edge (16) of the respective guide vane (6) and the oncoming flow edge (17) of the respective rotor blade (8) that is measured in the axial direction and is varied along a height (H) of a gas path (12) running axially between the blade rows (5, 7) of this stage (10), said height being measured radially.

    摘要翻译： 流体流动发动机（特别是涡轮发动机）具有至少一个具有多个导向叶片（6）的至少一个导向叶片排（5）和至少一个具有多个转子叶片的转子叶片排（7） 8）。 一个导向叶片排（5）和一个转子叶片排（7），其相对于工作气体流（11）直接位于下游，一起形成流体流动引擎（1）的台（10）。 为了减小转子叶片（8）上的负载，导叶（6）和转子叶片（8）至少在一个阶段（10）中协调，使得在相应的导向叶片（6）之间的参考相对位置， 和相应的转子叶片（8）之间，在相应导向叶片（6）的出流边缘（16）和迎风轮（6）的迎面流动边缘（17）之间存在轴向距离（B）和周向距离（C） 相应的转子叶片（8），其沿轴向测量并且沿着在该台（10）的叶片排（5,7）之间轴向延伸的气体路径（12）的高度（H）而变化，所述高度为 径向测量

    Method of removing casting defects
    3.
    发明授权
    Method of removing casting defects 有权
    去除铸件缺陷的方法

    公开(公告)号：US07169242B2

    公开(公告)日：2007-01-30

    申请号：US10923023

    申请日：2004-08-23

    申请人： John Fernihough ,  Matthias Hoebel ,  Maxim Konter

    发明人： John Fernihough ,  Matthias Hoebel ,  Maxim Konter

    IPC分类号： B22D27/20

    CPC分类号： F01D5/005 ,  B22D19/10 ,  B22D27/045 ,  B23K31/02 ,  B23K2101/001 ,  B23P6/007 ,  C30B11/00 ,  C30B13/00 ,  C30B29/52 ,  C30B33/00 ,  F05D2300/606

    摘要： A method for removing casting defects (5) from an article (1) with an oriented microstructure can include locating at least one casting defect (5) and melting the casting defect (5) locally by a heat source (7) to a depth at least as great as the casting defect (5) itself. The molten material can then be solidified epitaxially with respect to the surrounding oriented microstructure of the article (1) in a way that the resulting solidified area is substantially free of any defect.

    摘要翻译： 从具有取向微结构的制品（1）去除铸造缺陷（5）的方法可以包括定位至少一个铸造缺陷（5），并且通过热源（7）局部熔化铸造缺陷（5）至 至少与铸造缺陷（5）本身一样大。 熔融材料然后可以相对于制品（1）的周围取向微结构外延固化，使得所得固化区域基本上没有任何缺陷。

    Emergency cooling system for a thermally loaded component
    4.
    发明授权
    Emergency cooling system for a thermally loaded component 失效
    用于热负荷组件的紧急冷却系统

    公开(公告)号：US07077622B2

    公开(公告)日：2006-07-18

    申请号：US10694738

    申请日：2003-10-29

    申请人： Jan Ehrhard ,  Maxim Konter ,  Shailendra Naik ,  Ulrich Rathmann

    发明人： Jan Ehrhard ,  Maxim Konter ,  Shailendra Naik ,  Ulrich Rathmann

    IPC分类号： F01D21/12

    CPC分类号： F01D25/12 ,  F01D5/18 ,  F01D5/186 ,  F05D2260/202 ,  F23R3/005

    摘要： In an emergency cooling system (17) for a component (1) which is subject to thermal load in operation, in, e.g., a turbine, the component (1) has a wall (3) which, in operation, is acted on by heat on a first wall side (14) and is acted on by a flow of cooling fluid (11) on a second wall side (15). The wall (3) has at least one emergency cooling opening (12) which is closed off by a plug (16) and through which cooling fluid flows from the second wall side (15) to the first wall side (14) when the plug (16) is absent. The plug (16) is designed so as to melt at a predetermined temperature. The plug (16) is a body which is produced separately from the component (1), the plug (16) being inserted into the emergency cooling opening (12), in which it is connected to the component (1).

    摘要翻译： 在用于在运行中经受热负荷的部件（1）的紧急冷却系统（17）中，例如在涡轮机中，部件（1）具有壁（3），其在操作中由 在第一壁侧（14）上的热量被第二壁侧（15）上的冷却流体（11）流动。 所述壁（3）具有至少一个紧急冷却开口（12），所述紧急冷却开口（12）由所述塞子（16）封闭，并且当所述塞子（16）从所述第二壁侧（15）流动到所述第一壁侧 （16）不存在。 插头（16）设计成在预定温度下熔化。 插头（16）是与部件（1）分开制造的主体，插头插入紧急冷却开口（12）中，连接到部件（1）。

    Hot gas component of a turbomachine including an embedded channel
    7.
    发明授权
    Hot gas component of a turbomachine including an embedded channel 有权
    包括嵌入通道的涡轮机的热气体组分

    公开(公告)号：US08210815B2

    公开(公告)日：2012-07-03

    申请号：US12629245

    申请日：2009-12-02

    申请人： Cyrille Bezencon ,  Bernd Fehrmann ,  Matthias Hoebel ,  Maxim Konter ,  Wilfried Kurz ,  Jean-Daniel Wagnière

    发明人： Cyrille Bezencon ,  Bernd Fehrmann ,  Matthias Hoebel ,  Maxim Konter ,  Wilfried Kurz ,  Jean-Daniel Wagnière

    IPC分类号： F01D5/18

    CPC分类号： C30B29/52 ,  B23P15/02 ,  B23P15/04 ,  C30B13/24 ,  F01D5/187

    摘要： A component, especially a hot gas component of a turbomachine, has at least one passage (7, 7′), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7′) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

    摘要翻译： 特别是涡轮机的热气体组分的组分具有至少一个通道（7,7'），特别是冷却通道，其被嵌入在涡轮机的部件（1）的外壁（5）中并且基本上 平行于部件（1）的表面（6）延伸。 部件（1）具有基体（8）和至少一个涂覆在外部的基体上的涂层（9），并且通道（7,7'）一方面由空腔形成 形成在基体（8）中，另一方面通过涂层（9）朝向部件（1）的表面（6）封闭。

    SEAL IN GAS TURBINE
    8.
    发明申请
    SEAL IN GAS TURBINE 有权
    密封在气体涡轮机

    公开(公告)号：US20090081027A1

    公开(公告)日：2009-03-26

    申请号：US12236995

    申请日：2008-09-24

    申请人： Alexander KHANIN ,  Arkadi Fokine ,  Maxim Konter ,  Sergey Vorontsov

    发明人： Alexander KHANIN ,  Arkadi Fokine ,  Maxim Konter ,  Sergey Vorontsov

    IPC分类号： F02C7/28 ,  F02C7/24 ,  F01D11/00

    CPC分类号： F01D11/001 ,  F01D11/006 ,  F05D2240/57 ,  F16J15/061 ,  F16J15/0887

    摘要： A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

    摘要翻译： 用于燃气轮机的密封组件布置在具有多个弯曲部的转子隔热罩的槽中。 该组件包括彼此重叠的四个密封部分，并相对于涡轮转子沿轴向，径向和圆周方向延伸。 保持装置保持一个密封部分的径向部分，允许所述密封部分的有限运动独立于另一个密封部分。 独立的运动确保各个密封部分与转子隔热罩的所有配合表面的接触以及改进的密封功能，而与转子隔热罩的位移和涡轮机部件的公差无关。

    Monocrystalline alloys with controlled partitioning
    10.
    发明申请
    Monocrystalline alloys with controlled partitioning 审中-公开
    具有受控分配的单晶合金

    公开(公告)号：US20050224144A1

    公开(公告)日：2005-10-13

    申请号：US10994202

    申请日：2004-11-19

    申请人： Tresa Pollock ,  Qiang Feng ,  Laura Rowland ,  Maxim Konter ,  Peter Holmes

    发明人： Tresa Pollock ,  Qiang Feng ,  Laura Rowland ,  Maxim Konter ,  Peter Holmes

    IPC分类号： C22C19/05 ,  F01D5/28 ,  F01D25/00

    CPC分类号： C22C19/057 ,  F01D5/28 ,  F01D25/005 ,  F05D2300/607

    摘要： Nickel-based superalloys, for fabrication of monocrystalline turbine components to be used in industrial and aircraft turbine engines, having the following composition (in wt %): 5.6-8.1% Al, 4.1-14.1% Ru, 6.1-9.9% Ta, 3.6-7.5% Re, and the remaining balance Ni. The partitioning of alloying elements can be controlled to achieve a wide range of precipitate shapes and exceptional resistance to degradation under high temperature exposure conditions.

    摘要翻译： 用于制造用于工业和飞机涡轮发动机的单晶涡轮机部件的镍基超级合金具有以下组成（以重量％计）：5.6-8.1％Al，4.1-14.1％Ru，6.1-9.9％Ta，3.6 -7.5％Re，剩余余量为Ni。 可以控制合金元素的分配，以实现大范围的沉淀形状和在高温暴露条件下出色的耐劣化性。