公开(公告)号：US20110264413A1

公开(公告)日：2011-10-27

申请号：US13030301

申请日：2011-02-18

申请人： Alexander Stankowski ,  Lukas Emanuel Rickenbacher ,  Simone Hövel

发明人： Alexander Stankowski ,  Lukas Emanuel Rickenbacher ,  Simone Hövel

IPC分类号： G06F17/50

CPC分类号： B23P6/005 ,  F01D5/005 ,  F05D2230/23 ,  F05D2230/238

摘要： In a method for repairing and/or upgrading a component (10′), preferably of a gas turbine, especially a blade (10′), which component has been deformed during operation, a simplification with cost advantages is achieved by a first nominal CAD model (M1) of the non-deformed component (10) being made available, by the deformed component (10′) being measured, and by the first CAD-model (M1), with the aid of the data determined on the deformed component (10′), being transformed into a second CAD model (M2) of the deformed component (10′) by morphing. A cutting line, which determines a cut-out in the component (10′), and also an insert piece, which can be inserted in the cut-out, is established in the second CAD model (M2). A cut-out is introduced into the component (10′) in accordance with the cutting line, an insert piece for inserting in the cut-out is manufactured in accordance with the cutting line, the manufactured insert piece is inserted in the cut-out, and the inserted insert piece is connected to the component (10′) in a materially bonding manner.

摘要翻译： 在用于修复和/或升级组件（10'）的方法中，优选地是在操作期间已经变形的燃气轮机，特别是叶片（10'），通过第一标称CAD来实现具有成本优势的简化 通过被测量的变形部件（10'）和第一CAD模型（M1），借助于在变形部件上确定的数据使非变形部件（10）的型号（M1）可用， （10'），通过变形转换成变形部件（10'）的第二CAD模型（M2）。 在第二CAD模型（M2）中建立了切割线，其确定部件（10'）中的切口以及可插入切口中的插入件。 根据切割线将切口引入部件（10'）中，根据切割线制造用于插入切口的插入件，将制造的插入件插入切口 并且插入的插入件以物质接合方式连接到部件（10'）。

公开(公告)号：US08156649B2

公开(公告)日：2012-04-17

申请号：US12420578

申请日：2009-04-08

申请人： Simone Hövel ,  Alexander Stankowski ,  Günter Ambrosy ,  Matthias Hoebel ,  Alexander Schnell ,  Hans Bissig ,  Rainer Kurtz

发明人： Simone Hövel ,  Alexander Stankowski ,  Günter Ambrosy ,  Matthias Hoebel ,  Alexander Schnell ,  Hans Bissig ,  Rainer Kurtz

IPC分类号： B23P6/00

CPC分类号： B23P6/005 ,  B23K1/0018 ,  B23K1/0056 ,  B23K9/0026 ,  B23K10/00 ,  B23K26/0093 ,  B23K28/02 ,  B23K2101/001 ,  F01D5/005 ,  F05D2230/235 ,  F05D2230/80 ,  Y10T29/49318 ,  Y10T29/49728 ,  Y10T29/49732

摘要： A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.

摘要翻译： 提供了一种用于不延伸通过部件的厚度的缺陷的燃气涡轮发动机热气体部件修复方法。 通过在部件的表面中加工空腔来去除第一缺陷。 制造在空腔内配合的优惠券，例如在内表面上涂覆有钎焊介质，然后通过诸如激光金属成形之类的接合方法与部件接合。 在后续的热处理过程中，关节保持优惠券，从而不需要固定助剂。 在热处理之前，可以将另外的钎焊介质施加到与组件重叠的试样表面上。 单独的热处理，将试样钎焊到部件上，并将钎焊介质钎焊到试样的外表面上，然后用于完成修复。

公开(公告)号：US09901983B2

公开(公告)日：2018-02-27

申请号：US12915920

申请日：2010-10-29

申请人： Simone Hövel ,  Alexander Stankowski ,  Lukas Rickenbacher

发明人： Simone Hövel ,  Alexander Stankowski ,  Lukas Rickenbacher

IPC分类号： B23K26/00 ,  B22F3/00 ,  B22F3/105 ,  B22F5/00 ,  B22F5/04 ,  B22F7/06 ,  B22F7/08

CPC分类号： B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F7/062 ,  B22F7/08 ,  B22F2999/00 ,  Y02P10/295 ,  B22F3/1035

摘要： In a method for manufacturing an article (1), particularly a prototype of a product or component, a tool prototype or spare part, by using selected laser melting, for the application onto the article (1) of a layer (13) or portion of a second metallic material, which is different from the material of the first metallic powder (4), a tape (12), sheet (14), foil or three-dimensional pre-form (18) of a second material is applied to the article (1) and is heated by a focused laser or electron beam (6) to a specified temperature such that the tape (12), sheet (14), foil or pre-form, respectively, are made molten by the electron laser beam (6), wherein the focused beam (6) is applied to a given area corresponding to a selected cross-sectional area of the model of the article (1) under formation of a new layer or part made of second material integral with the article (1).

公开(公告)号：US20110099809A1

公开(公告)日：2011-05-05

申请号：US12915951

申请日：2010-10-29

申请人： Simone Hövel ,  Günter Ambrosy ,  Matthias Höbel

发明人： Simone Hövel ,  Günter Ambrosy ,  Matthias Höbel

IPC分类号： B23P17/00

CPC分类号： F01D5/005 ,  B23P6/005 ,  F05D2230/80 ,  Y10T29/49229 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49732 ,  Y10T29/49734 ,  Y10T29/49771

摘要： A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10). A higher degree of precision and automation can be achieved, because the worn out location is measured/scanned with a 3-D scanning/measuring system (20) to get the actual geometry of the missing zone (18), especially as a CAD data; the nominal geometry for the insert is defined by the actual geometry of the worn out location, with respect to certain defined gap tolerances; the actual geometry of the insert is measured during the manufacture of the insert; the nominal geometry and the actual geometry of the insert are compared; and an adaptive machining operation of the insert is carried out based on the results from the comparison between the actual and nominal geometries of the insert.

摘要翻译： 一种用于修理燃气涡轮机部件的方法包括：在所述燃气涡轮机部件（10）上识别所述燃气涡轮机部件（10）损坏的磨损位置; 去除损坏的位置，从而形成缺失区域（18）; 制造适合于缺失区（18）的插入件; 将插入物放入缺失区域（18）中; 调整所述燃气轮机部件（10）中的所述插入件; 并将调整好的插入件接合到燃气轮机部件（10）上。 可以实现更高的精度和自动化程度，因为用3维扫描/测量系统（20）测量/扫描磨损的位置以获得缺失区域（18）的实际几何形状，特别是作为CAD数据 ; 相对于某些限定的间隙公差，插入件的标称几何形状由磨损位置的实际几何形状定义; 在插入件的制造期间测量插入件的实际几何形状; 比较插入物的名义几何和实际几何形状; 并且基于插入件的实际和标称几何形状的比较的结果来执行插入件的自适应加工操作。

公开(公告)号：US20120018115A1

公开(公告)日：2012-01-26

申请号：US13009941

申请日：2011-01-20

申请人： SIMONE HÖVEL ,  ALEXANDER STANKOWSKI ,  LUKAS RICKENBACHER

发明人： SIMONE HÖVEL ,  ALEXANDER STANKOWSKI ,  LUKAS RICKENBACHER

IPC分类号： B22D23/06 ,  B22D25/02 ,  B22D27/02

CPC分类号： B22F3/1055 ,  B22F5/003 ,  B22F7/00 ,  B33Y10/00 ,  B33Y70/00 ,  Y02P10/295

摘要： A process produces a 3-dimensional component (16) by selective laser melting (SLM), in which the component (16) is formed on a foundation with a surface, e.g., a platform (10) or a support, which in particular is a component of the same type which has already been produced previously, by successively melting layers of a first metal powder to form a sequence of stacked layers. The process is substantially simplified and made more flexible by virtue of the fact that the separation of the finished component (16) from the surface of the platform (10) or the support thereof is simplified by providing a separating layer (11) between the component (16) and the platform (10) or the support, this separating layer making it possible to separate the finished component (16) from the platform (10) or the support without damaging the finished component (16).

摘要翻译： 一种方法通过选择性激光熔化（SLM）产生三维组件（16），其中组件（16）形成在具有表面的基础上，例如平台（10）或支撑件，其特别地是 通过连续地熔化第一金属粉末的层以形成层叠的顺序的先前已经生产的相同类型的组分。 由于通过在组件（16）之间提供分离层（11）来简化最终部件（16）与平台（10）的表面或其支撑件的分离，因此该过程被大大简化并变得更加灵活 （16）和平台（10）或支撑件，该分离层使得可以将成品部件（16）与平台（10）或支撑件分离，而不会损坏最终部件（16）。

公开(公告)号：US20110106290A1

公开(公告)日：2011-05-05

申请号：US12915920

申请日：2010-10-29

申请人： Simone HÖVEL ,  Alexander Stankowski ,  Lukas Rickenbacher

发明人： Simone HÖVEL ,  Alexander Stankowski ,  Lukas Rickenbacher

IPC分类号： G06F17/00

CPC分类号： B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F7/062 ,  B22F7/08 ,  B22F2999/00 ,  Y02P10/295 ,  B22F3/1035

摘要： In a method for manufacturing an article (1), particularly a prototype of a product or component, a tool prototype or spare part, by using selected laser melting, for the application onto the article (1) of a layer (13) or portion of a second metallic material, which is different from the material of the first metallic powder (4), a tape (12), sheet (14), foil or three-dimensional pre-form (18) of a second material is applied to the article (1) and is heated by a focused laser or electron beam (6) to a specified temperature such that the tape (12), sheet (14), foil or pre-form, respectively, are made molten by the electron laser beam (6), wherein the focused beam (6) is applied to a given area corresponding to a selected cross-sectional area of the model of the article (1) under formation of a new layer or part made of second material integral with the article (1).

摘要翻译： 在通过使用选择的激光熔化的制品（1）的制造方法，特别是产品或部件的原型，工具原型或备件，用于施加到层（13）或部分（13）的制品（1）上 与第一金属粉末（4）的材料不同的第二金属材料的第二材料的带（12），片（14），箔或三维预成型件（18）被施加到 物品（1），并被聚焦的激光或电子束（6）加热到指定的温度，使得带（12），片（14），箔或预成型分别由电子激光器熔化 光束（6），其中聚焦光束（6）被施加到对应于所述制品（1）的模型的所选横截面区域的给定区域，在形成由与所述第一材料 第1条）。

公开(公告)号：US08978249B2

公开(公告)日：2015-03-17

申请号：US12915951

申请日：2010-10-29

申请人： Simone Hövel ,  Günter Ambrosy ,  Matthias Höbel

发明人： Simone Hövel ,  Günter Ambrosy ,  Matthias Höbel

IPC分类号： B23P6/00 ,  F01D5/00

CPC分类号： F01D5/005 ,  B23P6/005 ,  F05D2230/80 ,  Y10T29/49229 ,  Y10T29/49318 ,  Y10T29/49336 ,  Y10T29/49732 ,  Y10T29/49734 ,  Y10T29/49771

摘要： A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10). A higher degree of precision and automation can be achieved, because the worn out location is measured/scanned with a 3-D scanning/measuring system (20) to get the actual geometry of the missing zone (18), especially as a CAD data; the nominal geometry for the insert is defined by the actual geometry of the worn out location, with respect to certain defined gap tolerances; the actual geometry of the insert is measured during the manufacture of the insert; the nominal geometry and the actual geometry of the insert are compared; and an adaptive machining operation of the insert is carried out based on the results from the comparison between the actual and nominal geometries of the insert.

摘要翻译： 一种用于修理燃气涡轮机部件的方法包括：在所述燃气涡轮机部件（10）上识别所述燃气涡轮机部件（10）损坏的磨损位置; 去除损坏的位置，从而形成缺失区域（18）; 制造适合于缺失区（18）的插入件; 将插入物放入缺失区域（18）中; 调整所述燃气轮机部件（10）中的所述插入件; 并将调整好的插入件接合到燃气轮机部件（10）上。 可以实现更高的精度和自动化程度，因为用3维扫描/测量系统（20）测量/扫描磨损的位置以获得缺失区域（18）的实际几何形状，特别是作为CAD数据 ; 相对于某些限定的间隙公差，插入件的标称几何形状由磨损位置的实际几何形状定义; 在插入件的制造期间测量插入件的实际几何形状; 比较插入物的名义几何和实际几何形状; 并且基于插入件的实际和标称几何形状的比较的结果来执行插入件的自适应加工操作。

公开(公告)号：US08610027B2

公开(公告)日：2013-12-17

申请号：US13009941

申请日：2011-01-20

申请人： Simone Hövel ,  Alexander Stankowski ,  Lukas Rickenbacher

发明人： Simone Hövel ,  Alexander Stankowski ,  Lukas Rickenbacher

IPC分类号： B23K26/14 ,  B22D27/02

CPC分类号： B22F3/1055 ,  B22F5/003 ,  B22F7/00 ,  B33Y10/00 ,  B33Y70/00 ,  Y02P10/295

摘要： A process produces a 3-dimensional component (16) by selective laser melting (SLM), in which the component (16) is formed on a foundation with a surface, e.g., a platform (10) or a support, which in particular is a component of the same type which has already been produced previously, by successively melting layers of a first metal powder to form a sequence of stacked layers. The process is substantially simplified and made more flexible by virtue of the fact that the separation of the finished component (16) from the surface of the platform (10) or the support thereof is simplified by providing a separating layer (11) between the component (16) and the platform (10) or the support, this separating layer making it possible to separate the finished component (16) from the platform (10) or the support without damaging the finished component (16).

摘要翻译： 一种方法通过选择性激光熔化（SLM）产生三维组件（16），其中组件（16）形成在具有表面的基础上，例如平台（10）或支撑件，其特别地是 通过连续地熔化第一金属粉末的层以形成层叠的顺序的先前已经生产的相同类型的组分。 由于通过在组件（16）之间提供分离层（11）来简化最终部件（16）与平台（10）的表面或其支撑件的分离，因此该过程被大大简化并变得更加灵活 （16）和平台（10）或支撑件，该分离层使得可以将成品部件（16）与平台（10）或支撑件分离，而不会损坏最终部件（16）。

公开(公告)号：US20110099810A1

公开(公告)日：2011-05-05

申请号：US12916032

申请日：2010-10-29

申请人： Alexander STANKOWSKI ,  Simone HÖVEL ,  Lukas RICKENBACHER ,  Matthias HÖBEL ,  Günter AMBROSY

发明人： Alexander STANKOWSKI ,  Simone HÖVEL ,  Lukas RICKENBACHER ,  Matthias HÖBEL ,  Günter AMBROSY

IPC分类号： B23P17/00

CPC分类号： F01D5/005 ,  B22F7/062 ,  B22F2999/00 ,  B23K2101/001 ,  B23P6/005 ,  F05D2230/13 ,  F05D2230/80 ,  F05D2250/20 ,  Y02P10/295 ,  Y10T29/49229 ,  B22F3/1055

摘要： A method for repairing an ex-service gas turbine component (10) includes the steps of: removing a damaged section (13) from the gas turbine component (10), manufacturing a 3-D article, which fits in the gas turbine component (10) to replace the removed damaged section (13), and joining the gas turbine component (10) and the 3-D article inserted therein. Reduced cost, improved flexibility and productivity, and simplified handling are achieved by removing the damaged section (13) in the form of a cut-out section along a split line (14) as one single cut-out piece (15), measuring the cut-out piece (15) to obtain the actual non-parametric geometry data set of the cut-out piece (15), and manufacturing the 3-D article based on the geometry data set of the cut-out piece (15).

摘要翻译： 一种维修燃气轮机组件（10）的方法，包括以下步骤：从燃气轮机部件（10）中取出损坏的部分（13），制造适合燃气轮机部件（3）的3-D制品 10），以更换已拆除的损坏部分（13），并且连接燃气轮机部件（10）和插入其中的3-D制品。 通过沿着分割线（14）将作为切割部分的形式的损坏部分（13）作为单个切割件（15）移除，测量成本，改进的柔性和生产率以及简化的处理 切割件（15），以获得切割件（15）的实际非参数几何数据集，并且基于切割件（15）的几何数据集来制造3-D制品。