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1. 发明授权

US08821116B2 Abradable coating system 有权
标题翻译：耐磨涂层系统
公开(公告)号：US08821116B2
公开(公告)日：2014-09-02
申请号：US12915978
申请日：2010-10-29
申请人： Sophie Duval , Piero-Daniele Grasso , Sven Olliges , Joergen Ferber , Alexander Stankowski
发明人： Sophie Duval , Piero-Daniele Grasso , Sven Olliges , Joergen Ferber , Alexander Stankowski
IPC分类号： F01D11/12 , F01D5/00 , F01D5/28
CPC分类号： F01D11/122 , F01D5/005 , F01D5/284 , F01D11/125 , F05D2230/90 , F05D2300/21 , F05D2300/6012 , F05D2300/603 , F05D2300/612 , F05D2300/615 , Y02T50/67 , Y02T50/672
摘要： An abradable coating system (2-8) for a turbine or a compressor is proposed has at least one layer of woven or non-woven tissue (15) or foam made of: ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof. A free-standing preformed element (18) has at least one layer of such a woven or non-woven tissue or foam is filled with fillers and/or binder. A method prepares such a system. Finally, a method for the repair of an abradable coating portion of a turbine or the compressor component (9) includes in a first optional step that the damaged portion is at least partly removed and/or cleaned and/or surface treated, and in a second step at least one free-standing preformed abradable coating element (18) or a complete abradable coating system is attached to the component (9), preferably by using a matrix, wherein for example only a center part (2) or a fraction of a center part (2) is replaced.
摘要翻译：提出了一种用于涡轮机或压缩机的可磨损涂层系统（2-8），其具有至少一层机织或非织造组织（15）或由陶瓷，玻璃，玻璃陶瓷，陶瓷 - 金属复合材料制成的泡沫或泡沫其组合。独立的预成型元件（18）具有至少一层这样的机织或非织造组织或泡沫填充有填料和/或粘合剂。一种方法准备这样的系统。最后，用于修复涡轮机或压缩机部件（9）的可磨损涂覆部分的方法包括在第一任选步骤中，损伤部分至少部分地被去除和/或清洁和/或表面处理，并且在第二步，优选通过使用基质将至少一个独立的预成形的可磨损涂层元件（18）或完整的可磨损涂层系统附接到部件（9），其中例如仅仅是中心部分（2）或部分更换中心部分（2）。

2. 发明申请

US20110103940A1 ABRADABLE COATING SYSTEM 有权
标题翻译：不可磨损的涂层系统
公开(公告)号：US20110103940A1
公开(公告)日：2011-05-05
申请号：US12915978
申请日：2010-10-29
申请人： Sophie Duval , Piero-Daniele Grasso , Sven Olliges , Joergen Ferber , Alexander Stankowski
发明人： Sophie Duval , Piero-Daniele Grasso , Sven Olliges , Joergen Ferber , Alexander Stankowski
IPC分类号： F01D11/12 , B32B37/16
CPC分类号： F01D11/122 , F01D5/005 , F01D5/284 , F01D11/125 , F05D2230/90 , F05D2300/21 , F05D2300/6012 , F05D2300/603 , F05D2300/612 , F05D2300/615 , Y02T50/67 , Y02T50/672
摘要： An abradable coating system (2-8) for a turbine or a compressor is proposed has at least one layer of woven or non-woven tissue (15) or foam made of: ceramic, glass, glass-ceramic, ceramic-metal composite and combinations thereof. A free-standing preformed element (18) has at least one layer of such a woven or non-woven tissue or foam is filled with fillers and/or binder. A method prepares such a system. Finally, a method for the repair of an abradable coating portion of a turbine or the compressor component (9) includes in a first optional step that the damaged portion is at least partly removed and/or cleaned and/or surface treated, and in a second step at least one free-standing preformed abradable coating element (18) or a complete abradable coating system is attached to the component (9), preferably by using a matrix, wherein for example only a center part (2) or a fraction of a center part (2) is replaced.
摘要翻译：提出了一种用于涡轮机或压缩机的可磨损涂层系统（2-8），其具有至少一层机织或非织造组织（15）或由陶瓷，玻璃，玻璃陶瓷，陶瓷 - 金属复合材料制成的泡沫或泡沫其组合。独立的预成型元件（18）具有至少一层这样的机织或非织造组织或泡沫填充有填料和/或粘合剂。一种方法准备这样的系统。最后，用于修复涡轮机或压缩机部件（9）的可磨损涂覆部分的方法包括在第一任选步骤中，损伤部分至少部分地被去除和/或清洁和/或表面处理，并且在第二步，优选通过使用基质将至少一个独立的预成形的可磨损涂层元件（18）或完整的可磨损涂层系统附接到部件（9），其中例如仅仅是中心部分（2）或部分更换中心部分（2）。

3. 发明授权

US08356482B2 Methods for the protection of a thermal barrier coating system and methods for the renewal of such a protection 有权
标题翻译：保护热障涂层系统的方法和更新这种保护的方法
公开(公告)号：US08356482B2
公开(公告)日：2013-01-22
申请号：US12420123
申请日：2009-04-08
申请人： Sophie Duval , Piero-Daniele Grasso , Alexander Stankowski
发明人： Sophie Duval , Piero-Daniele Grasso , Alexander Stankowski
IPC分类号： F01K13/02 , F01D1/02
CPC分类号： C23C4/18 , C23C26/00 , C23C28/00 , C23C28/30 , F05B2230/90 , Y10T428/31678
摘要： A method for the application and/or renewal of a protection for a thermal barrier coating system of a heat engine involves a thermal barrier coating system that includes a bond coat layer (2) and a thermal barrier coating layer (3) of porous structure (4), wherein the bond coat layer (2) is located between and in contact with a base metal (1) of a heat engine component and with the thermal barrier coating layer (3) and bonds the thermal barrier coating layer (3) to the base metal (1). At least one substance is applied inside the engine as a liquid or carried by a liquid by spraying and/or by flowing it across a hot gas exposed surface (9) of the barrier coating layer (3) of the heat engine component mounted within the heat engine in the assembled state prior to the initial start-up of the engine, before the first operation interval, or during a washing cycle of the thermal engine and/or at the end of an operation interval, before a subsequent operation interval, wherein the substance covers and/or at least partly penetrates into the porous structure (4), and concomitantly or subsequently hardens to remain within the pores (4) and/or on the upper surface (9) of the thermal barrier coating layer. Preferably, but not necessarily, for the application, the turbine washing equipment of the engine is used.
摘要翻译：用于热引擎的热障涂层系统的保护的应用和/或更新的方法包括热障涂层系统，其包括粘结涂层（2）和多孔结构的隔热涂层（3） 4），其中所述粘合涂层（2）位于热发动机部件的基体金属（1）之间并与所述热障涂层（3）接触并将所述热障涂层（3）结合到贱金属（1）。至少一种物质作为液体施用在发动机内部或通过喷射和/或通过将其流过安装在所述发动机内部的发动机部件的阻隔涂层（3）的热气体暴露表面（9）上而被液体携带在第一操作间隔之前或在热机的洗涤循环期间和/或在操作间隔结束之前，在发动机的初始启动之前，在发动机的初始起动之前，或在操作间隔结束之前的组装状态下的热机，其中该物质覆盖和/或至少部分地渗透到多孔结构（4）中，并伴随或随后硬化以保留在隔热涂层的孔（4）和/或上表面（9）上。优选但不是必须的，对于该应用，使用发动机的涡轮洗涤设备。

4. 发明授权

US08221825B2 Comprehensive method for local application and local repair of thermal barrier coatings 有权
标题翻译：局部应用和热障涂层局部修复的综合方法
公开(公告)号：US08221825B2
公开(公告)日：2012-07-17
申请号：US12427186
申请日：2009-04-21
申请人： Daniel Reitz , Sophie Duval , Piero-Daniele Grasso , Alexander Stankowski , Fernando Manuel Santos Silverio
发明人： Daniel Reitz , Sophie Duval , Piero-Daniele Grasso , Alexander Stankowski , Fernando Manuel Santos Silverio
IPC分类号： C03B29/00 , C04B33/34 , C23C16/52 , B05D3/00 , B32B43/00 , B05C13/00 , B41N1/24
CPC分类号： F01D5/005 , C23C24/08 , C23C28/042 , C23C28/322 , C23C28/3455 , F05D2230/30 , F05D2260/80
摘要： A method for the local initial application of a thermal barrier coating layer (3), or for the local repair of coating defects and/or deteriorations of components (1) in the hot gas path of a gas turbine engine, which components are coated with a thermal barrier coating layer, includes at least the following steps: (I) in the case of repair, normally overall inspection of the whole component (1) for the determination of the location of defect/deterioration, as well as of corresponding type of defect/deterioration of each place for a multitude of locations of the component (1); (II) if needed, preparation of the surface in at least one location; (III) local application of a ceramic tissue together with a wet chemical thermal barrier coating layer deposition material for the formation of a patch (5) of ceramic matrix composite; (IV)a intermediate inspection of the patch and/or the surface; (IV)b in the case of a repetitive and/or multi-step repair method, subsequent layer application of a ceramic tissue together with a wet chemical thermal barrier coating layer deposition material for the formation of a patch (5) of ceramic matrix composite at this location; (V) if needed, surface finishing at the at least one location; and (VI) final inspection of the at least one location. Steps (IV)a, (V) and (VI) can be omitted with the provision that at least one of steps (IV)a or (VI) is carried out.
摘要翻译：一种用于局部初始施加热障涂层（3）的方法，或用于在燃气涡轮发动机的热气路径中局部修复涂层缺陷和/或部件（1）的劣化的方法，所述部件被涂覆热障涂层至少包括以下步骤：（I）在维修的情况下，通常整体检查整个部件（1）以确定缺陷/劣化的位置，以及相应类型的组件（1）的多个位置的每个位置的缺陷/劣化; （II）如果需要，在至少一个位置准备表面; （III）陶瓷组织与湿化学热障涂层沉积材料的局部应用，用于形成陶瓷基复合材料的贴片（5）; （IV）补片和/或表面的中间检查; （IV）b，在重复和/或多步骤修复方法的情况下，随后将陶瓷组织与湿化学热障涂层沉积材料一起施加以形成陶瓷基体复合材料的贴片（5）在这个位置; （V），如果需要，在至少一个位置处进行表面处理; 和（VI）至少一个位置的最终检查。可以省略步骤（IV）a，（V）和（VI），条件是执行步骤（IV）a或（VI）中的至少一个。

5. 发明申请

US20100242477A1 METHODS FOR THE PROTECTION OF A THERMAL BARRIER COATING SYSTEM AND METHODS FOR THE RENEWAL OF SUCH A PROTECTION 有权
标题翻译：保护热障涂层系统的方法及其保护方法
公开(公告)号：US20100242477A1
公开(公告)日：2010-09-30
申请号：US12420123
申请日：2009-04-08
申请人： Sophie Duval , Piero-Daniele Grasso , Alexander Stankowski
发明人： Sophie Duval , Piero-Daniele Grasso , Alexander Stankowski
IPC分类号： F01K13/00
CPC分类号： C23C4/18 , C23C26/00 , C23C28/00 , C23C28/30 , F05B2230/90 , Y10T428/31678
摘要： A method for the application and/or renewal of a protection for a thermal barrier coating system of a heat engine involves a thermal barrier coating system that includes a bond coat layer (2) and a thermal barrier coating layer (3) of porous structure (4), wherein the bond coat layer (2) is located between and in contact with a base metal (1) of a heat engine component and with the thermal barrier coating layer (3) and bonds the thermal barrier coating layer (3) to the base metal (1). At least one substance is applied inside the engine as a liquid or carried by a liquid by spraying and/or by flowing it across a hot gas exposed surface (9) of the barrier coating layer (3) of the heat engine component mounted within the heat engine in the assembled state prior to the initial start-up of the engine, before the first operation interval, or during a washing cycle of the thermal engine and/or at the end of an operation interval, before a subsequent operation interval, wherein the substance covers and/or at least partly penetrates into the porous structure (4), and concomitantly or subsequently hardens to remain within the pores (4) and/or on the upper surface (9) of the thermal barrier coating layer. Preferably, but not necessarily, for the application, the turbine washing equipment of the engine is used.
摘要翻译：用于热引擎的热障涂层系统的保护的应用和/或更新的方法包括热障涂层系统，其包括粘结涂层（2）和多孔结构的隔热涂层（3） 4），其中所述粘合涂层（2）位于热发动机部件的基体金属（1）之间并与所述热障涂层（3）接触并将所述热障涂层（3）结合到贱金属（1）。至少一种物质作为液体施用在发动机内部或通过喷射和/或通过将其流过安装在所述发动机内部的发动机部件的阻隔涂层（3）的热气体暴露表面（9）上而被液体携带在第一操作间隔之前或在热机的洗涤循环期间和/或在操作间隔结束之前，在发动机的初始起动之前，在发动机的初始启动之前，或在操作间隔结束之前的组装状态下的热机，其中该物质覆盖和/或至少部分地渗透到多孔结构（4）中，并伴随或随后硬化以保留在隔热涂层的孔（4）和/或上表面（9）上。优选但不是必须的，对于该应用，使用发动机的涡轮洗涤设备。

6. 发明授权

US08113787B2 Turbomachine blade with erosion and corrosion protective coating and method of manufacturing 有权
标题翻译：涡轮机刀片具有腐蚀和腐蚀保护涂层及其制造方法
公开(公告)号：US08113787B2
公开(公告)日：2012-02-14
申请号：US11765599
申请日：2007-06-20
申请人： Marie-Gilles Barril , Piero-Daniele Grasso , Alexander Stankowski
发明人： Marie-Gilles Barril , Piero-Daniele Grasso , Alexander Stankowski
IPC分类号： F01D5/28
CPC分类号： F01D5/288 , F04D29/023 , F04D29/324 , F05D2240/303 , F05D2260/95 , F05D2300/121 , F05D2300/6032 , F05D2300/611 , F05D2300/615 , Y10T29/49986
摘要： A turbomachine blade (1) includes a blade body (2) and a corrosion and erosion protective multilayered coating (11) bonded thereto, the multilayered coating (11) including an erosion resistant first layer (3) at least covering a corrosion and erosion critical area (5) of the blade body (2) and a sacrificial second layer (4) provided over the first layer (3) at least covering the first layer (3), preferably covering the blade totally. A method of manufacturing such a turbomachine blade includes the steps of providing a blade and depositing the erosion resistant first layer on the blade body so as to cover at least the corrosion and erosion critical area, followed by depositing the sacrificial second layer over the first layer at least covering the first layer.
摘要翻译：涡轮机叶片（1）包括刀片体（2）和与其结合的腐蚀和侵蚀保护性多层涂层（11），所述多层涂层（11）包括至少覆盖腐蚀和侵蚀关键的耐侵蚀的第一层（3）刀片体（2）的区域（5）和设置在第一层（3）上的至少覆盖第一层（3）的牺牲性第二层（4），优选地全部覆盖刀片。一种制造这种涡轮机叶片的方法包括以下步骤：提供叶片并将抗侵蚀的第一层沉积在叶片体上，以便至少覆盖腐蚀和侵蚀临界区域，然后在第一层上沉积牺牲第二层至少覆盖第一层。

7. 发明申请

US20080317601A1 Turbomachine Blade With Erosion and Corrosion Protective Coating and Method of Manufacturing 有权
标题翻译：具有侵蚀和腐蚀保护涂层的涡轮机刀片及其制造方法
公开(公告)号：US20080317601A1
公开(公告)日：2008-12-25
申请号：US11765599
申请日：2007-06-20
申请人： Marie-Gilles Barril , Piero-Daniele Grasso , Alexander Stankowski
发明人： Marie-Gilles Barril , Piero-Daniele Grasso , Alexander Stankowski
IPC分类号： F01D5/28
CPC分类号： F01D5/288 , F04D29/023 , F04D29/324 , F05D2240/303 , F05D2260/95 , F05D2300/121 , F05D2300/6032 , F05D2300/611 , F05D2300/615 , Y10T29/49986
摘要： A turbomachine blade (1) includes a blade body (2) and a corrosion and erosion protective multilayered coating (11) bonded thereto, the multilayered coating (11) including an erosion resistant first layer (3) at least covering a corrosion and erosion critical area (5) of the blade body (2) and a sacrificial second layer (4) provided over the first layer (3) at least covering the first layer (3), preferably covering the blade totally. A method of manufacturing such a turbomachine blade includes the steps of providing a blade and depositing the erosion resistant first layer on the blade body so as to cover at least the corrosion and erosion critical area, followed by depositing the sacrificial second layer over the first layer at least covering the first layer.
摘要翻译：涡轮机叶片（1）包括刀片体（2）和与其结合的腐蚀和侵蚀保护性多层涂层（11），所述多层涂层（11）包括至少覆盖腐蚀和侵蚀关键的耐侵蚀的第一层（3）刀片体（2）的区域（5）和设置在第一层（3）上的至少覆盖第一层（3）的牺牲性第二层（4），优选地全部覆盖刀片。一种制造这种涡轮机叶片的方法包括以下步骤：提供叶片并将抗侵蚀的第一层沉积在叶片体上，以便至少覆盖腐蚀和侵蚀临界区域，然后在第一层上沉积牺牲第二层至少覆盖第一层。

8. 发明申请

US20110106290A1 METHOD OF APPLYING MULTIPLE MATERIALS WITH SELECTIVE LASER MELTING ON A 3D ARTICLE 有权
标题翻译：在3D文章上应用选择性激光熔化的多种材料的方法
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）。

9. 发明申请

US20100175724A1 DEVICE FOR CLEANING OXIDIZED OR CORRODED COMPONENTS IN THE PRESENCE OF A HALOGENOUS GAS MIXTURE 有权
标题翻译：在恶臭气体混合物存在下清洁氧化或腐蚀的组分的装置
公开(公告)号：US20100175724A1
公开(公告)日：2010-07-15
申请号：US12352641
申请日：2009-01-13
申请人： Ansgar Lutterman , Alexander Stankowski , Karsten Bindernagel
发明人： Ansgar Lutterman , Alexander Stankowski , Karsten Bindernagel
IPC分类号： B08B5/00
CPC分类号： F01D5/005 , C23G5/00 , F05D2230/11
摘要： A device for cleaning oxidized or corroded components (26), especially gas turbine components which are exposed to hot gases, in the presence of a halogenous gas, includes a cleaning retort which is designed in the shape of a boiler or cylinder and into which, indirectly or directly, leads a feed line which is connected via a flow control unit to a gas reservoir which stores the halogenous gas, and in which a device for gas distribution is integrated. The flow control unit has a gas volume control valve (5), a heat exchanger unit (9), and also a gas volume measuring unit (6) in sequence along the throughflow direction of the halogenous gas which flows through the feed line. Furthermore, a gas distribution in the retort directs the halogenous gas directly to the components which are to be cleaned.
摘要翻译：一种用于清洁氧化或腐蚀的部件（26）的设备，特别是在存在卤素气体的情况下暴露于热气体的燃气涡轮机部件，包括设计成锅炉或汽缸形式的清洗蒸馏器，间接地或直接地将通过流量控制单元连接的进料管线引导到储存有卤素气体的气体储存器，并且其中集成了用于气体分配的装置。流量控制单元具有气体量控制阀（5），热交换器单元（9），以及气体体积测量单元（6），其顺次沿着流过供给管线的卤素气体的流动方向。此外，蒸馏器中的气体分布将卤素气体直接引导到待清洁的部件。

10. 发明授权

US08881965B2 Braze alloy for high-temperature brazing and methods for repairing or producing components using a braze alloy 有权
标题翻译：用于高温钎焊的钎焊合金和使用钎焊合金修复或制造部件的方法
公开(公告)号：US08881965B2
公开(公告)日：2014-11-11
申请号：US13232120
申请日：2011-09-14
申请人： Alexander Stankowski , Daniel Beckel
发明人： Alexander Stankowski , Daniel Beckel
IPC分类号： B23K31/02 , B23P6/00 , B23K1/00 , B23K35/30 , B23K35/02 , C22C19/03 , C22C19/07 , F01D5/00
CPC分类号： B23K1/0018 , B23K35/0244 , B23K35/3033 , B23K35/3046 , B23K2101/001 , B23P6/00 , B23P6/005 , C22C19/03 , C22C19/07 , F01D5/005 , F05D2230/238 , Y10T29/49318 , Y10T428/12181
摘要： In a Ni-based, Co-based, or Ni—Co-based braze alloy (1) for high-temperature brazing of components (7) of modular structure and for repairing damaged components (7) which are formed of single crystal or directionally solidified superalloys using said braze alloy (1), the braze alloy has a first metallic powder component (2) having particle sizes in the nanometer range and a second metallic powder component (3) having particle sizes in the micrometer range. The surface of the particles of the second powder component (3) is thinly coated with particles of the first powder component (2). The braze alloy (1) additionally includes grain boundary stabilizing elements as alloying elements. In addition, melting point depressants can be present in the braze alloy (1) in a commercially common quantity or with a considerably increased proportion. Both the melting temperature of the braze alloy (1) and the probability of recrystallization are advantageously reduced.
摘要翻译：在用于模块化结构的部件（7）的高温钎焊和用于修复由单晶或定向形成的损坏部件（7）的Ni基，Co基或Ni-Co基钎焊合金（1）使用所述钎焊合金（1）的固化超合金，所述钎焊合金具有粒径在纳米范围内的第一金属粉末成分（2）和粒度在微米范围内的第二金属粉末成分（3）。第二粉末组分（3）的颗粒表面被薄的第一粉末组分（2）的颗粒涂覆。钎焊合金（1）还包括作为合金元素的晶界稳定元件。此外，熔点降低剂可以以商业上普遍的量或大大增加的比例存在于钎焊合金（1）中。钎焊合金（1）的熔融温度和重结晶的可能性都有利地降低。

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