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    METHOD FOR COATING A TURBINE BLADE
    1.
    发明申请
    METHOD FOR COATING A TURBINE BLADE 有权
    涂布涡轮叶片的方法

    公开(公告)号：US20120125980A1

    公开(公告)日：2012-05-24

    申请号：US13386074

    申请日：2010-07-08

    申请人： Karl-Hermann Richter ,  Ulrich Knott ,  Piotr Kowalczyk

    发明人： Karl-Hermann Richter ,  Ulrich Knott ,  Piotr Kowalczyk

    IPC分类号： B23K31/02

    CPC分类号： F01D5/225 ,  F01D5/005

    摘要： A method for hardfacing a metal component surface (14, 16), especially a shroud surface of a turbine blade made of a TiAl alloy, with at least one metal material (18, 20), in particular a Co—Cr alloy. The hardfacing coating is produced separately from the component surface and is then joined to the component surface in a high-temperature soldering process. A turbine blade including such a hardfacing coating, primarily in a shroud region (2).

    摘要翻译： 一种用至少一种金属材料（18,20）特别是Co-Cr合金表面硬化金属部件表面（14,16），特别是由TiAl合金制成的涡轮叶片的护罩表面的方法。 表面硬化层与零件表面分开制造，然后在高温焊接工艺中与组件表面接合。 涡轮叶片，其包括主要在护罩区域（2）中的这种表面硬化涂层。

    Method for coating a turbine blade
    2.
    发明授权
    Method for coating a turbine blade 有权
    喷涂涡轮叶片的方法

    公开(公告)号：US08393528B2

    公开(公告)日：2013-03-12

    申请号：US13386074

    申请日：2010-07-08

    申请人： Karl-Hermann Richter ,  Ulrich Knott ,  Piotr Kowalczyk

    发明人： Karl-Hermann Richter ,  Ulrich Knott ,  Piotr Kowalczyk

    IPC分类号： B23K1/00 ,  B23K1/19

    CPC分类号： F01D5/225 ,  F01D5/005

    摘要： A method for hardfacing a metal component surface (14, 16), especially a shroud surface of a turbine blade made of a TiAl alloy, with at least one metal material (18, 20), in particular a Co—Cr alloy. The hardfacing coating is produced separately from the component surface and is then joined to the component surface in a high-temperature soldering process. A turbine blade including such a hardfacing coating, primarily in a shroud region (2).

    摘要翻译： 一种用至少一种金属材料（18,20）特别是Co-Cr合金表面硬化金属部件表面（14,16），特别是由TiAl合金制成的涡轮叶片的护罩表面的方法。 表面硬化层与零件表面分开制造，然后在高温焊接工艺中与组件表面接合。 涡轮叶片，其包括主要在护罩区域（2）中的这种表面硬化涂层。

    Methods of repairing worn blade tips of compressor and turbine blades
    4.
    发明授权
    Methods of repairing worn blade tips of compressor and turbine blades 失效
    修复压缩机和涡轮叶片磨损刀片尖端的方法

    公开(公告)号：US5913555A

    公开(公告)日：1999-06-22

    申请号：US950869

    申请日：1997-10-15

    申请人： Karl-Hermann Richter ,  Ulrich Knott

    发明人： Karl-Hermann Richter ,  Ulrich Knott

    IPC分类号： B23K1/002 ,  B23P6/00 ,  F01D5/00 ,  B23P15/00

    CPC分类号： B23P6/005 ,  B23K1/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/49318 ,  Y10T29/4973 ,  Y10T29/49737 ,  Y10T29/49748

    摘要： In a method of repairing worn blade tips of compressor or turbine blades, the worn blade tip (4) is first removed from the remaining blade portion (2) at a standardized height (h). The actual geometry of the end of the remaining blade portion (2) at the height (h) is measured, for example by optical digital image processing means. A repair part (4') is cut from a plate or sheet of repair material having a thickness (d) essentially corresponding to the difference between the nominal finished height (H) of the repaired turbine blade (1) and the standardized height (h) of the remaining blade portion (2) undergoing repair. The repair part (4') is cut to have a contour corresponding to the measured actual geometry of the end of the remaining blade portion (2) at the standardized cut-off height (h), for example using a laser cutting process CNC-controlled by the acquired data representing the actual blade geometry. Finally, the repair part (4') is attached to the end of the remaining blade portion (2), for example by welding or soldering, and preferably by induction soldering with a solder foil (5) interposed between the repair part (4') and the remaining blade portion. The resulting repair is a smooth transition from the remaining blade portion to the repair part, substantially matching the original new blade shape, without requiring finish machining of the joint.

    摘要翻译： 在修复压缩机或涡轮机叶片的磨损的叶片尖端的方法中，磨损的叶片尖端（4）首先从标准高度（h）从剩余叶片部分（2）移除。 例如通过光学数字图像处理装置来测量剩余刀片部分（2）在高度（h）的端部的实际几何形状。 修理部件（4'）从具有厚度（d）的修补材料的板或片切割，所述厚度（d）基本上对应于修理的涡轮叶片（1）的标称成品高度（H）与标准化高度（h ）剩余刀片部分（2）进行修理。 修剪部分（4'）被切割成具有对应于在标准化的切断高度（h）处的剩余刀片部分（2）的端部的测量的实际几何形状的轮廓，例如使用激光切割过程CNC- 由获取的数据控制，表示实际的叶片几何形状。 最后，修理部分（4'）例如通过焊接或焊接附接到剩余刀片部分（2）的端部，并且优选地通过用位于修复部分（4'）之间的焊料箔（5）进行感应焊接， ）和剩余的刀片部分。 所产生的修复是从剩余的刀片部分到修复部分的平滑过渡，基本上与原来的新刀片形状匹配，而不需要对接头进行精加工。

    Method for joining components using a brazing technique
    8.
    发明申请
    Method for joining components using a brazing technique 审中-公开
    使用钎焊技术接合部件的方法

    公开(公告)号：US20090200361A1

    公开(公告)日：2009-08-13

    申请号：US12310859

    申请日：2007-09-05

    申请人： Ulrich Knott ,  Walter Gieg ,  Anton Reichart

    发明人： Ulrich Knott ,  Walter Gieg ,  Anton Reichart

    IPC分类号： B23K1/20 ,  B23K11/11

    CPC分类号： B23K1/0008 ,  B23K1/0004 ,  B23K11/115 ,  B23K11/163 ,  B23K28/02 ,  B23K2101/18

    摘要： A method for joining components using a brazing technique, namely relatively thin-walled components, in particular sheet-metal panels, which are not inherently stable and thus are susceptible to deformation, comprising at least the following steps: a) preparing at least two planar and relatively thin-walled components to be joined together, and a brazing foil; b) placing the brazing foil between the components to be joined together; c) fixing in position the components to be joined together by tack welding in such a way that a tack welding of the components, between which the brazing foil is placed, is carried out at at least one position that is spaced apart from an edge of the components; d) joining the fixed-in-position components by brazing.

    摘要翻译： 一种使用钎焊技术连接部件的方法，即相对薄壁的部件，特别是金属板，其固有地不稳定并且因此容易变形，至少包括以下步骤：a）制备至少两个平面 和相邻的薄壁部件接合在一起，以及钎焊箔; b）将钎焊箔放置在待接合的部件之间; c）通过定位焊接固定待接合的部件的位置，使得在其之间布置钎焊箔的部件的定位焊接在至少一个位置上，所述至少一个位置与 组件; d）通过钎焊连接定位固定部件。