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    VANE FOR A COMPRESSOR OR A TURBINE OF AN AIRCRAFT ENGINE, AIRCRAFT ENGINE COMPRISING SUCH A VANE AND A METHOD FOR COATING A VANE OF AN AIRCRAFT ENGINE
    4.
    发明申请
    VANE FOR A COMPRESSOR OR A TURBINE OF AN AIRCRAFT ENGINE, AIRCRAFT ENGINE COMPRISING SUCH A VANE AND A METHOD FOR COATING A VANE OF AN AIRCRAFT ENGINE 审中-公开
    压缩机的风扇或飞机发动机的涡轮机，包括这种风扇的飞机发动机和用于涂覆飞机发动机的空气的方法

    公开(公告)号：US20100143110A1

    公开(公告)日：2010-06-10

    申请号：US12513281

    申请日：2007-10-27

    申请人： Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling ,  Markus Uecker

    发明人： Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling ,  Markus Uecker

    IPC分类号： F01D9/02 ,  B05D5/00

    CPC分类号： C23C28/044 ,  C23C30/00 ,  F01D5/288

    摘要： An aircraft engine comprising a compressor and at least one turbine is disclosed. The compressor and the turbine are each provided with vanes, each of which has a blade that forms a suction side and a pressure side, where at least one first of the blades is coated with a protective layer in order to reduce the erosion or wear. The layer is applied such that at least two areas are formed that adjoin each other at a boundary line. The first area has a protective layer that has a substantially constant first thickness and the second area is free of the protective layer or has the protective layer with a substantially constant second thickness, the second thickness differing from the first thickness. The boundary line has at least two points, of which the connecting line differs from the course of the boundary line between the two points.

    摘要翻译： 公开了一种包括压缩机和至少一个涡轮机的飞机发动机。 压缩机和涡轮机各自设置有叶片，每个叶片具有形成吸力侧和压力侧的叶片，其中至少一个叶片的第一叶片被涂覆有保护层，以减少侵蚀或磨损。 施加该层，使得在边界线处形成彼此相邻的至少两个区域。 第一区域具有保持层，该保护层具有基本恒定的第一厚度，第二区域不含保护层，或具有基本上恒定的第二厚度的保护层，第二厚度与第一厚度不同。 边界线至少有两点，其连接线与两点之间的边界线的路线不同。

    Device for the Protection of Components Having A Flammable Titanium Alloy From Titanium Fire, and Method for the Production Thereof
    7.
    发明申请
    Device for the Protection of Components Having A Flammable Titanium Alloy From Titanium Fire, and Method for the Production Thereof 审中-公开
    用于保护具有钛火焰的易燃钛合金的部件的设备及其制造方法

    公开(公告)号：US20100143108A1

    公开(公告)日：2010-06-10

    申请号：US12449184

    申请日：2008-01-29

    申请人： Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling ,  Markus Uecker

    发明人： Thomas Uihlein ,  Wolfgang Eichmann ,  Falko Heutling ,  Markus Uecker

    IPC分类号： F04D29/54 ,  B32B15/04 ,  B32B5/14 ,  C23C14/34 ,  C23C16/00 ,  B05D1/00 ,  F04D29/38

    CPC分类号： C23C28/321 ,  C23C28/322 ,  C23C28/34 ,  C23C28/42 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T428/12458 ,  Y10T428/31678

    摘要： The use of titanium-based materials in the manufacturing of gas turbines, especially of engines, and, in particular, of compressors is made possible in that a device is devised that protects the components (guide vanes, guide vane stages, rotor blades, rotor blade stages) that are subject to the action of titanium fire and/or FODs by employing a layer system that includes at least two layers, is situated on the surface of the components to be protected, and is bonded thereto, as the case may be, via an adhesion-promoting layer is disclosed. The outermost layer is ceramic; the layer that is subjacent thereto is of metallic nature. Additional layers can optionally follow, ceramic and metallic layers alternating with one another. Moreover, a method is provided for producing the device. Through the at least partial use of titanium alloys, in particular for guide vanes of gas turbines, the weight of compressors can be significantly reduced in that the need for the nickel- or steel-based structural materials used under the related art is eliminated in favor of lighter titanium alloys.

    摘要翻译： 在制造燃气涡轮机，特别是发动机，特别是压缩机中使用钛基材料是可能的，因为设计了一种保护部件（导向叶片，导叶片，转子叶片，转子 通过使用包含至少两层的层系统而受到钛火和/或FOD的作用的刀片台）位于要保护的部件的表面上，并且根据情况可以粘合到其上 ，通过粘附促进层。 最外层是陶瓷; 其下面的层具有金属性质。 附加层可以任选地跟随，陶瓷和金属层彼此交替。 此外，提供了一种用于制造该装置的方法。 通过至少部分使用钛合金，特别是对于燃气轮机的导向叶片，可以显着地减少压缩机的重量，因为对现有技术中使用的基于镍或钢的结构材料的需求被消除 较轻的钛合金。

    EROSION PROTECTION COATING
    10.
    发明申请
    EROSION PROTECTION COATING 有权
    防腐保护涂料

    公开(公告)号：US20110045264A1

    公开(公告)日：2011-02-24

    申请号：US12988045

    申请日：2009-04-18

    申请人： Falko Heutling ,  Thomas Uihlein ,  Wolfgang Eichmann

    发明人： Falko Heutling ,  Thomas Uihlein ,  Wolfgang Eichmann

    IPC分类号： B32B7/02

    CPC分类号： C23C14/0641 ,  C23C14/027 ,  C23C28/044 ,  C23C28/048 ,  C23C28/42 ,  F01D5/284 ,  F01D5/288 ,  F05D2300/506 ,  Y10T428/24975 ,  Y10T428/24983

    摘要： The invention relates to an erosion protection coating (11), in particular, for gas turbine components, having a horizontally segmented and/or multi-layered construction. i.e., having at least one relatively hard layer (12) and having at least one relatively soft layer (13), wherein the relatively hard layer or each relatively hard layer as well as the relatively soft layer or each relatively soft layer are disposed on top of one another in an alternating manner, in such a way that an outer-lying layer, which forms an outer surface of the erosion protection coating, is formed as a relatively hard layer (12). According to the invention, the relatively hard layer or each relatively hard layer (12) as well as the relatively soft layer or each relatively soft layer (13) are formed as a ceramic layer in each case.

    摘要翻译： 本发明涉及具有水平分段和/或多层结构的用于燃气轮机部件的侵蚀保护涂层（11）。 即具有至少一个相对较硬的层（12）并且具有至少一个相对软的层（13），其中相对较硬的层或每个相对硬的层以及相对软的层或每个相对软的层设置在顶部 彼此以交替的方式，以形成侵蚀保护涂层的外表面的外层作为相对硬的层（12）形成。 根据本发明，在每种情况下，相对硬的层或每个相对硬的层（12）以及相对软的层或每个相对软的层（13）形成为陶瓷层。