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公开(公告)号：US5479704A
公开(公告)日：1996-01-02
申请号：US286695
申请日：1994-08-05
CPC分类号： B23P6/005 , B23K15/0053 , B23K26/28 , F01D5/005 , Y10T29/49318 , Y10T29/49336
摘要： A repair process for blades of turboengines damaged in the head or edge regions in which the damaged regions are first separated to leave an undamaged blade stump with an exposed, repair surface. The repair surface of the blade stump is prepared for butt welding and a repair plate of constant thickness which exceeds the maximum profile height of the blade by more than 50% is provided with a front surface adapted to the repair surface. This front surface of the repair plate is abutted against the repair surface and the blade stump and the repair blade are then butt welded. The weld joint and the repair plate are machined to the profile contour of the blade stump and to the desired blade profile. This process is used for the repair of blades of integral rotor disks of turboengines, particularly for blades of integral compressor impellers.
摘要翻译： 在头部或边缘区域损坏的涡轮机叶片的修复过程，其中损伤区域首先被分离以留下未损坏的刀片残端和暴露的修复表面。 制备刀片残端的修复表面用于对接焊接，并且具有超过叶片最大轮廓高度超过50％的恒定厚度的修复板设置有适于修复表面的前表面。 修复板的前表面与修复表面相接触，并将刀片残端和修补刀片对接。 焊接接头和修补板被加工成刀片残端的轮廓轮廓和所需的刀片轮廓。 该过程用于修复涡轮机的整体转子盘的叶片，特别是用于整体式压缩机叶轮的叶片。
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2.发明授权Process and apparatus for applying layers of material to a workpiece made of tiAl 有权用于将材料层施加到由tiAl制成的工件上的工艺和设备公开(公告)号：US09550255B2
公开(公告)日：2017-01-24
申请号：US13701682
申请日：2011-06-16
IPC分类号： B23K9/04 , B32B15/00 , B23K37/00 , B23K10/02 , B23K35/32 , F01D5/00 , F01D5/22 , F01D5/28 , B23K26/32
CPC分类号： B23K37/00 , B23K9/04 , B23K10/027 , B23K26/32 , B23K26/342 , B23K26/60 , B23K35/325 , B23K35/327 , B23K2103/10 , B23K2103/14 , B23K2103/18 , B23K2103/52 , F01D5/005 , F01D5/225 , F01D5/288 , F05D2230/31 , Y10T428/12639
摘要： A method for depositing material layers on a workpiece made of a material which contains a titanium aluminide includes the steps of: preparing the workpiece; heating the workpiece in a localized region by induction to a predefined preheating temperature; and depositing an additive, preferably in powder form, on the heated surface of the workpiece by build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding; the additive including a titanium aluminide.
摘要翻译： 在由含有铝化钛的材料制成的工件上沉积材料层的方法包括以下步骤：准备工件; 通过感应将局部区域中的工件加热到预定的预热温度; 并且通过堆积焊接，特别是激光积聚焊接，等离子体堆积焊接，微等离子体堆积焊接，TIG堆积焊接，在工件的被加热表面上沉积优选粉末形式的添加剂 或微型TIG堆焊; 所述添加剂包括钛铝化物。
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3.发明授权Device and method for the repair or production of blade tips of blades of a gas turbine, in particular of an aircraft engine 有权用于修理或生产燃气轮机叶片的叶片尖端的装置和方法，特别是飞机发动机公开(公告)号：US08584357B2
公开(公告)日：2013-11-19
申请号：US12519117
申请日：2007-12-05
IPC分类号： B21D53/78
CPC分类号： B23P6/007 , B22F3/1055 , B22F5/04 , B22F2003/1056 , B22F2998/00 , B23P15/02 , B33Y80/00 , F01D5/005 , F05D2230/40 , Y02P10/295 , Y10T29/49318 , Y10T29/49336 , B22F3/003
摘要： The invention relates to a device for the production or repair of a blade for a gas turbine, said device comprising: a holding device for holding a blade or an aerofoil of a blade; a lowering mechanism for lowering the blade or the aerofoil; a container for receiving power and/or for receiving the blade or the aerofoil; a heating device; and a radiation source, wherein the heating device is formed as an induction coil.
摘要翻译： 本发明涉及一种用于生产或修理用于燃气轮机的叶片的装置，所述装置包括：用于保持叶片的叶片或机翼的保持装置; 用于降低叶片或机翼的降低机构; 用于接收动力和/或用于接收叶片或机翼的容器; 加热装置; 和辐射源，其中所述加热装置形成为感应线圈。
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公开(公告)号：US20120125980A1
公开(公告)日：2012-05-24
申请号：US13386074
申请日：2010-07-08
IPC分类号： B23K31/02
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。
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5.发明申请公开(公告)号：US20110219616A1
公开(公告)日：2011-09-15
申请号：US13129295
申请日：2009-11-07
申请人： Erwin Bayer , Karl-Hermann Richter
发明人： Erwin Bayer , Karl-Hermann Richter
IPC分类号： B23P6/00
CPC分类号： B23P6/005 , B23K15/0006 , B23K20/129 , B23K2101/001 , F01D5/005 , F01D5/34 , F05D2230/232 , F05D2230/80 , Y02T50/672 , Y10T29/49316 , Y10T29/49318 , Y10T29/49321 , Y10T29/49323 , Y10T29/49719 , Y10T29/4973 , Y10T29/49798
摘要： The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored.
摘要翻译： 本发明涉及一种用于更换刀片集成盘的内盘元件的方法，其中刀片一体盘在接合区域中具有多个呈轴向通孔形式的凹槽。 该方法开始于填充轴向通孔，之后刀片集成盘的内盘元件与剩余刀片环分离。 接下来，将新的内部盘元件插入到剩余的刀片环中，并且新的内部盘元件和剩余的刀片环连接。 最后，轴向通孔恢复。
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公开(公告)号：US20100074755A1
公开(公告)日：2010-03-25
申请号：US12307497
申请日：2007-07-11
CPC分类号： B23P6/005 , B23K1/0018 , B23K26/28 , B23K28/02 , B23K2101/001 , F01D5/005 , F05D2230/232 , F05D2230/80 , Y02T50/673 , Y10T29/49318 , Y10T29/49321 , Y10T29/49336
摘要： A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour.
摘要翻译： 一种通过更换叶片轮廓的至少一部分来修复涡轮叶片的方法，该方法具有：a）制造替换叶片部分; b）用标准化的切割平面分离损坏的区域，留下剩余的刀片; c）将替换刀片部件与剩余刀片的实际几何形状匹配; d）通过焊接至少一个腹板和外部轮廓的焊接来将替换刀片部分连接或连接到剩余刀片。
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7.发明授权Method for integrally connecting blades and disks in order to form a blade-disk unit, as well as correspondingly produced blade-disk unit 有权用于一体地连接刀片和盘以形成刀片盘单元以及相应地生产的刀片盘单元的方法公开(公告)号：US09284848B2
公开(公告)日：2016-03-15
申请号：US13350504
申请日：2012-01-13
申请人： Karl-Hermann Richter
发明人： Karl-Hermann Richter
IPC分类号： F01D5/30
CPC分类号： F01D5/3061 , F05D2230/233 , F05D2230/234 , F05D2230/236 , F05D2230/237 , Y10T29/4932
摘要： A blade-disk unit for a turbine engine includes a disk and a plurality of blades which are integrally connected to the disk, a welding seam being disposed in the joining region between the blade and the disk, which welding seam is situated entirely either in the blade or in the disk.
摘要翻译： 用于涡轮发动机的叶片盘单元包括盘和与盘完全连接的多个叶片，焊缝设置在叶片和盘之间的接合区域中，该焊缝完全位于 刀片或磁盘。
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8.发明授权Method and apparatus for producing and/or repairing an integrally bladed rotor by inductive diffusion welding 有权通过感应扩散焊接生产和/或修复整体叶片转子的方法和装置公开(公告)号：US08375582B2
公开(公告)日：2013-02-19
申请号：US11815961
申请日：2006-02-04
申请人： Erwin Bayer , Ulrich Knott , Karl-Hermann Richter
发明人： Erwin Bayer , Ulrich Knott , Karl-Hermann Richter
CPC分类号： B23P6/005 , B23K20/023 , B23K2101/001 , Y10T29/49318 , Y10T29/49321 , Y10T29/49998
摘要： A method and apparatus for the fabrication and/or repair of an integrally bladed rotor, specifically of an integrally bladed gas turbine rotor, is disclosed. At least one rotor blade is joined to a main rotor body for fabrication and/or repair. The joining is carried out by diffusion welding.
摘要翻译： 公开了用于制造和/或修理整体叶片的转子，特别是整体叶片的燃气轮机转子的方法和装置。 至少一个转子叶片连接到主转子主体用于制造和/或修理。 通过扩散焊接进行接合。
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9.发明申请Method And Apparatus For Producing And/Or Repairing An Integrally Bladed Rotor By Inductive Diffusion Welding 有权通过感应扩散焊接生产和/或修复整体叶片转子的方法和装置公开(公告)号：US20080148566A1
公开(公告)日：2008-06-26
申请号：US11815961
申请日：2006-02-04
申请人： Erwin Bayer , Ulrich Knott , Karl-Hermann Richter
发明人： Erwin Bayer , Ulrich Knott , Karl-Hermann Richter
CPC分类号： B23P6/005 , B23K20/023 , B23K2101/001 , Y10T29/49318 , Y10T29/49321 , Y10T29/49998
摘要： A method and apparatus for the fabrication and/or repair of an integrally bladed rotor, specifically of an integrally bladed gas turbine rotor, is disclosed. At least one rotor blade is joined to a main rotor body for fabrication and/or repair. The joining is carried out by diffusion welding.
摘要翻译： 公开了用于制造和/或修理整体叶片的转子，特别是整体叶片的燃气轮机转子的方法和装置。 至少一个转子叶片连接到主转子主体用于制造和/或修理。 通过扩散焊接进行接合。
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10.发明授权公开(公告)号：US08667680B2
公开(公告)日：2014-03-11
申请号：US13129295
申请日：2009-11-07
申请人： Erwin Bayer , Karl-Hermann Richter
发明人： Erwin Bayer , Karl-Hermann Richter
IPC分类号： B21K25/00
CPC分类号： B23P6/005 , B23K15/0006 , B23K20/129 , B23K2101/001 , F01D5/005 , F01D5/34 , F05D2230/232 , F05D2230/80 , Y02T50/672 , Y10T29/49316 , Y10T29/49318 , Y10T29/49321 , Y10T29/49323 , Y10T29/49719 , Y10T29/4973 , Y10T29/49798
摘要： The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored.
摘要翻译： 本发明涉及一种用于更换刀片集成盘的内盘元件的方法，其中刀片一体盘在接合区域中具有多个呈轴向通孔形式的凹槽。 该方法开始于填充轴向通孔，之后刀片集成盘的内盘元件与剩余刀片环分离。 接下来，将新的内部盘元件插入到剩余的刀片环中，并且新的内部盘元件和剩余的刀片环连接。 最后，轴向通孔恢复。
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