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2834 条记录 (耗时 0.04 秒)

    TURBINE BLADE AIRFOIL
    91.
    发明申请
    TURBINE BLADE AIRFOIL 有权
    涡轮叶片飞行器

    公开(公告)号：US20120057981A1

    公开(公告)日：2012-03-08

    申请号：US12877701

    申请日：2010-09-08

    申请人： Timothy Charles Nash ,  Jason L. O'Hearn

    发明人： Timothy Charles Nash ,  Jason L. O'Hearn

    IPC分类号： F01D5/14

    CPC分类号： F01D5/141 ,  F01D5/143 ,  F05D2240/301 ,  F05D2240/80 ,  F05D2250/74 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673

    摘要： An airfoil comprises an external surface formed in substantial conformance with a plurality of cross sections. Each of the cross sections has an axial chord and an offset at a corresponding fractional span as set forth in Table 2. Each of the cross sections is described by a set of Cartesian coordinates defined at the corresponding fractional span as set forth in Table 4.

    摘要翻译： 翼型件包括基本上符合多个横截面形成的外表面。 每个横截面具有如表2所示的相应分数跨度的轴向弦和偏移。每个横截面由如表4所示的相应分数跨度定义的一组笛卡尔坐标来描述。

    COMPONENTS WITH CONFORMAL CURVED FILM HOLES AND METHODS OF MANUFACTURE
    92.
    发明申请
    COMPONENTS WITH CONFORMAL CURVED FILM HOLES AND METHODS OF MANUFACTURE 有权
    具有一致弯曲膜的组件及其制造方法

    公开(公告)号：US20120051941A1

    公开(公告)日：2012-03-01

    申请号：US12872559

    申请日：2010-08-31

    申请人： Ronald Scott Bunker

    发明人： Ronald Scott Bunker

    IPC分类号： F01D5/18 ,  B23P15/00

    CPC分类号： F01D5/186 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676

    摘要： A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an exit region at the second surface. The second surface has a non-planar curvature in the vicinity of the exit region. The film cooling hole is tapered at the exit region, such that the curvature of the film cooling hole in the exit region conforms to the non-planar curvature of the second surface, thereby forming a curved exit region. A method is also provided for forming at least one film cooling hole in the component. The method includes forming a straight section in the component wall, such that the straight section extends through the first surface, and tapering the film cooling hole, such that the curvature of the film cooling hole in the exit region conforms to the non-planar curvature of the second surface, thereby forming a curved exit region for the film cooling hole.

    摘要翻译： 提供部件并且包括包括第一和第二表面的至少一个壁。 至少一个薄膜冷却孔在第一表面和第二表面之间延伸穿过壁，并且在第二表面处具有出口区域。 第二表面在出口区域附近具有非平面曲率。 薄膜冷却孔在出口区域是锥形的，使得出口区域中的薄膜冷却孔的曲率符合第二表面的非平面曲率，从而形成弯曲的出射区域。 还提供了用于在部件中形成至少一个膜冷却孔的方法。 所述方法包括在所述部件壁上形成直线部分，使得所述直线部分延伸穿过所述第一表面，并且使所述膜冷却孔逐渐变细，使得所述出口区域中的所述膜冷却孔的曲率符合所述非平面曲率 从而形成用于膜冷却孔的弯曲出口区域。

    COMBUSTION CONTROLLER
    94.
    发明申请
    COMBUSTION CONTROLLER 有权
    燃烧控制器

    公开(公告)号：US20120023965A1

    公开(公告)日：2012-02-02

    申请号：US13180920

    申请日：2011-07-12

    申请人： Simon A. WEEKS ,  Christopher G. BRIGHT

    发明人： Simon A. WEEKS ,  Christopher G. BRIGHT

    IPC分类号： F02C7/22 ,  F02C1/00

    CPC分类号： F02M27/04 ,  F02C7/262 ,  F02C7/264 ,  F02C9/50 ,  Y02T50/67

    摘要： The present invention relates to a combustion controller for controlling the combustion of a flow of combustible and/or combusting fluid. The combustion controller comprises an inlet and an outlet which defines a flow path between them. A magnetic-field generator is arranged to generate a magnetic field across the flow path such that in use the fluid flows in the flow path through the magnetic field. As the fluid flows through the magnetic field an electric current is induced in the fluid. This results in energy being supplied to the fluid. This energy can assist is reignition. If the magnetic field is an alternating magnetic field then this induces an alternating current in the fluid. The frequency of this current can be controlled such that certain chemical reactions are either promoted or inhibited.

    摘要翻译： 本发明涉及一种用于控制可燃和/或燃烧流体的流动的燃烧的燃烧控制器。 燃烧控制器包括限定其间的流动路径的入口和出口。 磁场发生器布置成在流动路径上产生磁场，使得在使用中，流体在通过磁场的流动路径中流动。 当流体流过磁场时，在流体中产生电流。 这导致能量被供应到流体。 这种能量可以帮助是重燃。 如果磁场是交变磁场，则这会在流体中产生交流电流。 可以控制该电流的频率，使得某些化学反应被促进或抑制。

    Process for coating metallic surfaces with a multicomponent aqueous composition
    95.
    发明授权
    Process for coating metallic surfaces with a multicomponent aqueous composition 有权
    用多组分含水组合物涂覆金属表面的方法

    公开(公告)号：US08101014B2

    公开(公告)日：2012-01-24

    申请号：US12696696

    申请日：2010-01-29

    申请人： Thomas Kolberg ,  Manfred Walter ,  Peter Schubach

    发明人： Thomas Kolberg ,  Manfred Walter ,  Peter Schubach

    IPC分类号： C09D1/00 ,  C08K5/22 ,  C08K3/10 ,  C08K5/53 ,  C08K5/09

    CPC分类号： C09D5/084 ,  C08K3/10 ,  C08K5/0008 ,  C09D7/61 ,  C23C2222/20 ,  Y02T50/67 ,  Y10T428/31663

    摘要： The invention relates to a process for coating metallic surfaces with a composition containing silane/silanol/siloxane/polysiloxane, wherein, in addition to a) at least one compound selected from silanes, silanols, siloxanes and polysiloxanes, b) at least one compound containing titanium, hafnium, zirconium, aluminum and/or boron, and c) at least one type of cation selected from cations of metals of subgroups 1 to 3 and 5 to 8, including lanthanides, and of main group 2 of the periodic table of the elements, and/or at least one corresponding compound, the composition contains at least one substance d) selected from: d1) silicon-free compounds having at least one amino, urea and/or ureido group in each case, d2) anions of nitrite and/or compounds having at least one nitro group, d3) compounds based on peroxide, and d4) phosphorus-containing compounds, anions of at least one phosphate and/or anions of at least one phosphonate, as well as e) water, and f) optionally also at least one organic solvent. The invention further relates to corresponding aqueous compositions.

    摘要翻译： 本发明涉及一种用含有硅烷/硅烷醇/硅氧烷/聚硅氧烷的组合物涂覆金属表面的方法，其中除了a）至少一种选自硅烷，硅烷醇，硅氧烷和聚硅氧烷的化合物之外，b）至少一种含 钛，铪，锆，铝和/或硼，以及c）至少一种阳离子，其选自亚族1至3和5至8族的金属的阳离子，包括镧系元素，以及元素周期表的主族2的阳离子 元素和/或至少一种相应的化合物，所述组合物含有至少一种选自以下的物质d）：d1）在每种情况下具有至少一个氨基，脲和/或脲基的无硅化合物，d2）亚硝酸根阴离子 和/或具有至少一个硝基的化合物，d3）基于过氧化物的化合物和d4）含磷化合物，至少一种磷酸盐和/或至少一种膦酸盐的阴离子的阴离子，以及e）水，和 f）任选地还至少一个orga nic溶剂。 本发明还涉及相应的含水组合物。

    Coated turbine blade
    97.
    发明授权
    Coated turbine blade 有权
    涂层涡轮叶片

    公开(公告)号：US08075279B2

    公开(公告)日：2011-12-13

    申请号：US11895259

    申请日：2007-08-23

    申请人： Fathi Ahmad ,  Michael Dankert

    发明人： Fathi Ahmad ,  Michael Dankert

    IPC分类号： B64C11/24

    CPC分类号： F01D5/188 ,  F01D5/288 ,  F05D2230/31 ,  F05D2230/90 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

    摘要： The invention refers to a coated turbine blade for a gas turbine, having blade walls divided into sections with locally adapted material temperatures. The cooler material temperatures of the blade walls are at the points where the support ribs merge into the blade walls. The regions with higher material temperatures of the blade walls are at the positions where cavities are arranged inside the blade walls. This is achieved via a ceramic thermal barrier coating having different layer thicknesses that allow different material temperatures. The region of the surface of the blade wall which faces the working medium and lies opposite an internal rib has a thicker thermal barrier coating than a region of the surface of the blade wall which is cooled via a cooling medium that flows in the cavities. This results in homogenization of the material temperature in the connecting regions, which results in prolonged blade life.

    摘要翻译： 本发明涉及一种用于燃气轮机的涂覆涡轮机叶片，其具有被划分成具有局部适应材料温度的部分的叶片壁。 叶片壁的较冷的材料温度在支撑肋合并到叶片壁中的点处。 叶片壁的材料温度较高的区域位于叶片壁内空间的位置。 这通过具有允许不同材料温度的不同层厚度的陶瓷热障涂层来实现。 面对工作介质并且与内部肋相对的叶片表面的区域具有比通过在空腔中流动的冷却介质冷却的叶片壁表面的区域更厚的热障涂层。 这导致连接区域中的材料温度的均匀化，这导致刀片寿命延长。

    Heat transfer arrangement for fluid-washed surfaces
    98.
    发明申请
    Heat transfer arrangement for fluid-washed surfaces 有权
    流体冲洗表面的传热装置

    公开(公告)号：US20110296811A1

    公开(公告)日：2011-12-08

    申请号：US13067484

    申请日：2011-06-03

    申请人： David S. Knott ,  Alexis Lambourne ,  Andrew M. Rolt ,  Cosimo Buffone

    发明人： David S. Knott ,  Alexis Lambourne ,  Andrew M. Rolt ,  Cosimo Buffone

    IPC分类号： F02C7/047 ,  F28F13/18 ,  F01D5/08 ,  F28F7/00

    CPC分类号： F01D5/18 ,  B64D15/00 ,  F01D25/02 ,  F02C7/047 ,  F05D2220/325 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49353

    摘要： A heat transfer arrangement for a fluid-washed body having first and second ends and a fluid-washed surface extending there-between. The arrangement includes a heat transfer member extending from the first end at least part way along the body towards the second end. A heat source is arranged in use to heat the heat transfer member in the vicinity of the first end of the body. A plurality of thermal control layers are provided on the heat transfer member, each of the layers having a different thermal conductivity and being juxtaposed so as to create a thermal conductivity profile which varies along the length of the member. The arrangement may be used for prevention of icing of an aerofoil body such as a blade, vane or the like.

    摘要翻译： 用于具有第一和第二端部的流体冲洗体和在其之间延伸的流体冲洗表面的热传递装置。 该装置包括从第一端至少部分地沿主体朝向第二端延伸的传热构件。 热源设置在使用中以加热身体第一端附近的传热构件。 多个热控制层设置在传热构件上，每个层具有不同的导热性并且并置，以便产生沿构件的长度变化的热导率分布。 该装置可以用于防止诸如叶片，叶片等的翼面体的结冰。

    METHOD OF MACHINING ROTOR BLADE WEAR INDICATORS, AND ROTOR BLADE PLUG FOR IMPLEMENTING THE METHOD
    99.
    发明申请
    METHOD OF MACHINING ROTOR BLADE WEAR INDICATORS, AND ROTOR BLADE PLUG FOR IMPLEMENTING THE METHOD 有权
    用于加工转子叶片磨损指示器的方法和用于实施方法的转子叶片

    公开(公告)号：US20110296687A1

    公开(公告)日：2011-12-08

    申请号：US13150649

    申请日：2011-06-01

    申请人： Damien Hebuterne ,  Janvier Lecomte

    发明人： Damien Hebuterne ,  Janvier Lecomte

    IPC分类号： B23P15/04 ,  B23C1/00 ,  F16L55/11

    CPC分类号： B23K26/16 ,  B23K26/18 ,  F01D5/20 ,  F05D2230/13 ,  Y02T50/67 ,  Y02T50/673 ,  Y10T29/37 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49995 ,  Y10T29/5176

    摘要： A method for machining at least one aircraft gas turbine engine rotor (1) blade (2) wear indicator (41, 42, 43), comprising a step of machining the wear indicator (41, 42, 43) using a laser (L) so as to melt part of the blade (2), and a step of collecting the molten material of the blade (2). For preference, the method comprises a step of fitting a plug (8) into said bathtub squealer (23), said plug (8) comprising at least one cavity (81, 82, 83) for receiving the molten blade (2) material.

    摘要翻译： 一种用于加工至少一个飞机燃气涡轮发动机转子（1）刀片（2）磨损指示器（41,42,43）的方法，包括使用激光（L）加工磨损指示器（41,42,43）的步骤， 以熔化叶片（2）的一部分，以及收集叶片（2）的熔融材料的步骤。 优选地，该方法包括将塞子（8）装配到所述浴缸喷射器（23）中的步骤，所述塞子（8）包括用于接收熔融叶片（2）材料的至少一个空腔（81,82,83）。