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1. 发明授权

US09333589B2 Component and method for joining metal elements 有权
标题翻译：用于连接金属元素的组分和方法
公开(公告)号：US09333589B2
公开(公告)日：2016-05-10
申请号：US12225350
申请日：2007-03-14
申请人： Herbert Hanrieder , Alexander Gindorf , Reinhold Meier
发明人： Herbert Hanrieder , Alexander Gindorf , Reinhold Meier
IPC分类号： B23K13/01 , H05B6/22 , B23K20/02 , F01D5/30
CPC分类号： B23K20/021 , B23K2101/001 , F01D5/3061 , F05D2230/232 , Y10T428/12493
摘要： A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements.
摘要翻译：描述了一种组件，特别是燃气轮机的部件，其由至少两个金属结构元件组成，第一结构元件具有第一接合表面，第二结构元件具有第二接合表面，并且结构元件被连接通过其接合表面通过感应式高频压力焊接。其中一个接合表面被成形为与其它接合表面相比在外围加宽，并且响应于结构元件的接合而在连接区域中产生的镦锻变形基本上完全搁置在并且特别地在形成的外围套环上通过一个连接表面的外围加宽。描述了用于连接金属结构元件，特别是燃气轮机的结构元件的方法，用于连接结构元件的相应接合表面的感应式高频压力焊接。

2. 发明申请

US20090317548A1 GAS TURBINE COMPONENT WITH A THERMAL BARRIER COATING, THERMAL BARRIER COATING FOR A GAS TURBINE COMPONENT AND PROCESS FOR PRODUCING A THERMAL BARRIER COATING ON A GAS TURBINE COMPONENT 审中-公开
标题翻译：具有热障涂层的气体涡轮机组件，用于气体涡轮机组件的热障涂层和用于在气体涡轮机部件上生产热障涂层的方法
公开(公告)号：US20090317548A1
公开(公告)日：2009-12-24
申请号：US12376271
申请日：2007-07-31
申请人： Reinhold Meier
发明人： Reinhold Meier
IPC分类号： C23C16/00
CPC分类号： C23C30/00 , C23C14/083 , F01D5/08 , F01D5/284 , F01D5/288 , F05D2230/313 , F05D2230/90 , F05D2300/21 , F05D2300/2118 , F23R3/002 , Y02T50/67 , Y02T50/676 , Y02T50/6765
摘要： A gas turbine component of an aircraft engine having a base body, which comprises at least a first material, and a thermal barrier coating that is applied to the base body and consists of or includes an oxide ceramic, is disclosed. Micro-defects and/or nano-defects are included in the oxide ceramic in order to reduce the thermal conductivity of the thermal barrier coating.
摘要翻译：公开了一种具有基体的飞机发动机的燃气轮机部件，其包括至少第一材料和施加到基体上并由氧化物陶瓷构成或包括氧化物陶瓷的热障涂层。为了降低热障涂层的热导率，在氧化物陶瓷中包含微缺陷和/或纳米缺陷。

3. 发明授权

US07634854B2 Method for joining blades to blade roots or rotor disks when manufacturing and/or repairing gas turbine blades or integrally bladed gas turbine rotors 失效
标题翻译：在制造和/或修理燃气轮机叶片或整体叶片燃气轮机转子时，将叶片连接到叶片根部或转盘上的方法
公开(公告)号：US07634854B2
公开(公告)日：2009-12-22
申请号：US10570418
申请日：2005-06-30
申请人： Reinhold Meier
发明人： Reinhold Meier
IPC分类号： B23P6/00 , B23P19/04
CPC分类号： B23P6/002 , B23K26/24 , B23K33/004 , B23K2101/001 , B23P15/006 , F01D5/005 , F01D5/3061 , Y02T50/673 , Y10T29/49316 , Y10T29/49318 , Y10T29/49321 , Y10T29/49336 , Y10T29/49728
摘要： A method is provided for joining blades to blade roots or rotor disks when manufacturing and/or repairing gas turbine blades or integrally bladed gas turbine rotors. A blade and a blade root or rotor disk that is to be joined to the blade are supplied, and provided with a thickening in sections that are to be joined together. The sections of the blade and the blade root or rotor disk that are to be joined together are machined so as to form recesses and; c) are then aligned relative to each other, opposite recesses defining at least one groove-shaped seam preparation. The blade and the blade root or rotor disk are joined in the area of the or each seam preparation by means of laser power build-up welding and the joined blade and blade root or rotor disk are machined so as to provide a gas turbine blade or an integrally bladed gas turbine rotor having a predefined geometrical profile.
摘要翻译：提供了一种用于在制造和/或修理燃气涡轮叶片或整体叶片燃气轮机转子时将叶片接合到叶片根部或转子盘的方法。供给要连接到叶片的叶片和叶片根部或转子盘，并且设置有要连接在一起的部分的增厚部。要连接在一起的叶片和叶片根部或转子盘的部分被加工成形成凹部; c）然后相对于彼此对准，相对的凹部限定至少一个槽形接缝制备。叶片和叶片根部或转子盘通过激光发电焊接在该接缝制备区域或每个接缝制备区域中接合，并且对加入的叶片和叶片根部或转子盘进行加工，以便提供燃气轮机叶片或具有预定几何轮廓的整体叶片燃气轮机转子。

4. 发明授权

US07559728B2 Milling tool and method for milling recesses 失效
标题翻译：铣削刀具和铣削凹槽的方法
公开(公告)号：US07559728B2
公开(公告)日：2009-07-14
申请号：US10578702
申请日：2004-10-23
申请人： Reinhold Meier , Georg Moosrainer , Wilfried Schuette
发明人： Reinhold Meier , Georg Moosrainer , Wilfried Schuette
IPC分类号： B23C3/34
CPC分类号： B23C5/08 , B23C3/18 , B23C3/34 , B23C2220/366 , Y10T29/49318 , Y10T29/49325 , Y10T29/49995 , Y10T407/19 , Y10T409/303808 , Y10T409/304424
摘要： A milling tool which is used to mill recesses, in particular, circular-shaped grooves, in a workpiece is provided. The milling tool (10) is disposed on a disk-shaped or plate-shaped base body (14) and on at least one cutting body (15) arranged on the outer periphery of the base body (14). The cutting body or each cutting body (15) is inclined in relation to the disk-shaped base body or the plate-shaped base body (14).
摘要翻译：提供了用于在工件中研磨凹部，特别是圆形凹槽的铣削工具。铣刀（10）设置在盘状或板状的基体（14）上，以及配置在基体（14）的外周的至少一个切割体（15）上。切割体或每个切割体（15）相对于盘形基体或板状基体（14）倾斜。

5. 发明申请

US20090031564A1 METHOD OF REPAIRING A SHROUD SEGMENT OF A GAS TURBINE 审中-公开
标题翻译：修复气体涡轮机风力发电机组的方法
公开(公告)号：US20090031564A1
公开(公告)日：2009-02-05
申请号：US12093811
申请日：2006-11-14
申请人： Reinhold Meier
发明人： Reinhold Meier
IPC分类号： B23P6/00
CPC分类号： F01D5/005 , B23K20/021 , B23K2101/001 , B23P6/005 , F01D11/12 , F05D2230/22 , F05D2230/233 , F05D2230/234 , F05D2230/236 , F05D2230/90 , F05D2240/11 , Y02T50/67 , Y02T50/6765 , Y10T29/49238
摘要： A method for repairing a shroud segment of a gas turbine, in particular of an aircraft engine, having the steps: a) provision of a shroud segment to be repaired; b) removal of a damaged radially inner section of the shroud segment, so that after the removal of the damaged section the shroud segment has an inner radius; c) manufacture of a replacement section for the shroud segment, the replacement section having an outer radius matched to the inner radius of the shroud segment; d) alignment of the replacement section and the shroud segment; and e) joining of the replacement section to the shroud segment, the replacement section and the shroud segment being first welded to one another for this purpose at their edges in gas-tight fashion in a vacuum, and the surfaces of the replacement section and the shroud segment being subsequently diffusion-bonded to one another by hot isostatic pressing.
摘要翻译：一种用于修理燃气涡轮机，特别是飞行器发动机的护罩段的方法，具有以下步骤：a）提供待修理的护罩段; b）去除护罩段的损伤的径向内部部分，使得在损坏的部分移除之后，护罩段具有内半径; c）制造用于所述护罩段的更换部分，所述更换部分具有与所述护罩段的内半径匹配的外半径; d）更换部分和护罩部分的对准; 以及e）将替换部分连接到护罩段，替换部分和护罩段首先在真空中以气密方式在其边缘处彼此焊接在一起，并且替换部分和护罩段随后通过热等静压进行彼此扩散粘合。

6. 发明申请

US20070122606A1 Method for producing gas turbine components and component for a gas turbine 失效
标题翻译：燃气轮机部件的制造方法以及燃气轮机的部件
公开(公告)号：US20070122606A1
公开(公告)日：2007-05-31
申请号：US10581939
申请日：2004-11-24
申请人： Reinhold Meier , Erich Steinhardt
发明人： Reinhold Meier , Erich Steinhardt
IPC分类号： B32B3/26 , B32B3/00
CPC分类号： B22F3/1125 , B22F5/04 , B22F7/006 , B22F2998/00 , B22F2998/10 , B22F2999/00 , F01D5/28 , F05D2230/22 , Y02T50/672 , Y10T29/49337 , Y10T29/49339 , Y10T29/49341 , Y10T428/249953 , Y10T428/249974 , B22F5/10 , C22C1/10 , C22C49/14 , B22F3/20 , B22F3/1109 , B22F2207/13
摘要： A method for producing gas turbine components, in particular blades, blade sections or rotors with integral blades for a jet engine is provided. The method comprises at least the following steps: preparation of at least one metallic powder and at least one expanding agent; mixing of the metallic powder or each metallic powder with the expanding agent or each expanding agent; compression of the resultant mixture to form at least one semi-finished product; expansion of the semi-finished product or each semi-finished product by heating to achieve a defined degree of expansion; termination of the expansion process by cooling, once the defined degree of expansion has been reached.
摘要翻译：提供了一种用于制造具有用于喷气发动机的整体叶片的燃气轮机部件，特别是叶片，叶片部分或转子的方法。该方法至少包括以下步骤：制备至少一种金属粉末和至少一种发泡剂; 将金属粉末或各金属粉末与发泡剂或各发泡剂混合; 压缩所得混合物以形成至少一种半成品; 通过加热使半成品或每个半成品的膨胀达到规定的膨胀程度; 通过冷却终止膨胀过程，一旦达到确定的膨胀程度。

7. 发明申请

US20100283211A1 HONEYCOMB STRUCTURE 有权
标题翻译：蜂窝结构
公开(公告)号：US20100283211A1
公开(公告)日：2010-11-11
申请号：US12667857
申请日：2008-06-21
申请人： Reinhold Meier
发明人： Reinhold Meier
IPC分类号： F16J15/447 , B32B38/00
CPC分类号： F01D11/127 , F05D2250/191 , F05D2250/283 , Y10T156/1002 , Y10T428/24149
摘要： Disclosed is a honeycomb structure for non-hermetic rotor-stator and rotor-rotor seals in turbo machines. Said honeycomb structure comprises a plurality of at least predominantly radially oriented honeycomb cells which are separated by cell walls, are open on one side, cooperate with at least one sharp sealing edge that rotates relative to the honeycomb structure, and can yield relative to the sharp sealing edge by being deformed and/or material being removed therefrom when being touched. The walls of the honeycomb cells have holes according to a defined perforation pattern.
摘要翻译：公开了一种用于涡轮机中的非密封转子 - 定子和转子 - 转子密封的蜂窝结构。所述蜂窝结构包括多个至少主要是径向定向的蜂窝单元，其被单元壁隔开，在一侧开口，与至少一个相对于蜂窝结构旋转的锋利的密封边缘配合，并且相对于尖锐的当被接触时，通过变形和/或材料被从其中移除，密封边缘。蜂窝单元的壁具有根据限定的穿孔图案的孔。

8. 发明申请

US20090101634A1 Joining Method 审中-公开
标题翻译：加盟方式
公开(公告)号：US20090101634A1
公开(公告)日：2009-04-23
申请号：US12224256
申请日：2007-02-16
申请人： Reinhold Meier
发明人： Reinhold Meier
IPC分类号： B23K13/01
CPC分类号： B23K11/26 , B23K13/015 , B23K2101/001 , F01D5/3061 , F05D2230/232
摘要： A joining method, in particular for gas turbine components, is provided wherein applying inductive heating, using at least one inductor, to a joining zone of a first component section and a second component section; following and/or during the step of applying inductive heating, exerting a press force on the first component second and the second component section to weld the first and second component section together, additionally heating by a capacitor discharge of the joining zone of the first and second component sections.
摘要翻译：提供了一种特别是用于燃气涡轮机部件的接合方法，其中使用至少一个电感器将感应加热施加到第一部件部分和第二部件部分的接合区域; 在施加感应加热的步骤之后和/或期间，对第一部件第二部件部分和第二部件部分施加按压力，以将第一和第二部件部分焊接在一起，另外通过第一和第二部件接合区域的电容器放电第二组成部分。

9. 发明申请

US20060243709A1 Method and device for restoring and producing geometrically complex components 审中-公开
标题翻译：用于恢复和生成几何复杂组件的方法和装置
公开(公告)号：US20060243709A1
公开(公告)日：2006-11-02
申请号：US10547402
申请日：2003-12-23
申请人： Werner Born , Reinhold Meier , Ludwig Schaller
发明人： Werner Born , Reinhold Meier , Ludwig Schaller
IPC分类号： B23K26/28
CPC分类号： B23P6/005 , B23K26/28 , B23K26/38 , F01D5/005 , F05D2230/13 , F05D2230/80
摘要： A method is provided for restoring geometrically complex components having damage or defects in regions of limited access, in which damaged or defective pieces are cut out of the components and replacement pieces of the same kind are welded in, the cutting and the welding being performed with the aid of laser energy. Using a CNC-controlled laser beam, a damaged or defective piece is cut out of a component. Using a laser beam and the same path data, modified by a correction if necessary, a replacement piece is cut out of a repair part. Using a laser beam and the same path data as in A, the replacement piece is welded into the component. A space-saving special adapter is used in the three foregoing machining steps. During the first three machining steps, the component remains in the same clamped support.
摘要翻译：提供了一种用于恢复在有限访问区域中具有损伤或缺陷的几何复杂部件的方法，其中损坏或缺陷的部件被切割出部件，并且将相同类型的替换件焊接在一起，切割和焊接是用辅助激光能量。使用CNC控制的激光束，从部件中切出损坏或有缺陷的部件。使用激光束和相同的路径数据，如果需要，通过校正进行修改，则从维修部件切出更换件。使用激光束和与A中相同的路径数据，将替换件焊接到部件中。在上述三个加工步骤中使用节省空间的特殊适配器。在前三个加工步骤中，组件保持在相同的夹紧支撑中。

10. 发明授权

US06543134B2 Method for reconditioning blades 失效
公开(公告)号：US06543134B2
公开(公告)日：2003-04-08
申请号：US09987006
申请日：2001-11-13
申请人： Reinhold Meier
发明人： Reinhold Meier
IPC分类号： B23P1500
CPC分类号： B23P6/007 , B23K26/32 , B23K26/342 , B23K2101/34 , B23K2103/08 , B23K2103/14 , B23K2103/18 , B23K2103/26 , B23K2103/52 , F01D5/005 , F05D2230/10 , F05D2230/12 , F05D2230/13 , F05D2230/80 , Y10T29/49318 , Y10T29/49336 , Y10T29/49339 , Y10T29/49746
摘要： A method is disclosed for reconditioning blades for turbo-machinery that have a material deficiency resulting from wear and tear, damage, or dimensions that are smaller than specified, in which material is removed, at least from parts of the blade, and is replaced with new material. The actual geometry of the blade is measured at certain specific points and is stored. The desired geometry, or the desired profile in its desired position, is determined via data processing technology. The desired geometry is compared with the actual geometry, and in cases of significant deviations in position, is adjusted to coincide with the actual geometry. The adjusted desired geometry is mathematically reduced by a defined amount of coating to be removed. The calculated net geometry is actually produced via the removal of material, at least over part of the blade, and new material is applied to the finished net geometry, until the desired profile is achieved.

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