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公开(公告)号：US20100247309A1
公开(公告)日：2010-09-30
申请号：US12732359
申请日：2010-03-26
申请人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
发明人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
CPC分类号： F01D11/001 , F05D2240/57 , F16J15/3292
摘要： A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).
摘要翻译： 用于密封围绕轴线旋转的轴的层状密封件，特别是在燃气轮机中，包括多个薄片（13），所述多个薄片（13）彼此间隔开，并以轴为中心圆周排列并固定在其位置， 其中通过其表面的薄片（13）基本上平行于轴线定向。 通过薄片（13）在每种情况下具有形成结构（19,20,21）以便将薄片（13）定位和保持在层状密封件（12）中的事实来改善层状密封，其包括一个或多个 更侧向突出的支撑臂（19,20,21），其接合端板（15,16）的互补形成的凹部（25,26）。
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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。
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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
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。
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公开(公告)号：US08740572B2
公开(公告)日：2014-06-03
申请号：US12917114
申请日：2010-11-01
IPC分类号： F01D5/28
摘要： A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.
摘要翻译： 提供耐磨和抗氧化涡轮叶片以及用于生产叶片的方法。 主叶片部分的表面的至少部分设置有由抗氧化材料组成的至少一个第一保护涂层，第一抗氧化涂层是金属涂层，其任选被陶瓷热障涂层覆盖。 金属第一保护涂层至少布置在叶片尖端的内冠和外冠边缘处，而不是在径向外叶片尖端处。 涡轮叶片的径向外叶片尖端由第二单层或多层耐磨和抗氧化的保护涂层组成，其由激光金属成形构成并由磨料和粘合剂材料组成。 叶片尖端上的第二保护涂层至少部分地与第一金属保护涂层布置在外侧和/或内冠冠边缘处重叠。
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公开(公告)号：US08517673B2
公开(公告)日：2013-08-27
申请号：US12732359
申请日：2010-03-26
申请人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
发明人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
IPC分类号： F01D25/00
CPC分类号： F01D11/001 , F05D2240/57 , F16J15/3292
摘要： A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).
摘要翻译： 用于密封围绕轴线旋转的轴的层状密封件，特别是在燃气轮机中，包括多个薄片（13），所述多个薄片（13）彼此间隔开，并以轴为中心圆周排列并固定在其位置， 其中通过其表面的薄片（13）基本上平行于轴线定向。 通过薄片（13）在每种情况下具有形成结构（19,20,21）以便将薄片（13）定位和保持在层状密封件（12）中的事实来改善层状密封，其包括一个或多个 更侧向突出的支撑臂（19,20,21），其接合端板（15,16）的互补形成的凹部（25,26）。
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公开(公告)号：US20110099810A1
公开(公告)日：2011-05-05
申请号：US12916032
申请日：2010-10-29
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。
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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。
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公开(公告)号：US20110103968A1
公开(公告)日：2011-05-05
申请号：US12917114
申请日：2010-11-01
摘要： A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.
摘要翻译： 提供耐磨和抗氧化涡轮叶片以及用于生产叶片的方法。 主叶片部分的表面的至少部分设置有由抗氧化材料组成的至少一个第一保护涂层，第一抗氧化涂层是金属涂层，其任选被陶瓷热障涂层覆盖。 金属第一保护涂层至少布置在叶片尖端的内冠和外冠边缘处，而不是在径向外叶片尖端处。 涡轮叶片的径向外叶片尖端由第二单层或多层耐磨和抗氧化的保护涂层组成，其由激光金属成形构成并由磨料和粘合剂材料组成。 叶片尖端上的第二保护涂层至少部分地与第一金属保护涂层布置在外侧和/或内冠冠边缘处重叠。
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