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1. 发明申请

WO2010003404A2 METHOD FOR THE PRODUCTION OF INTEGRALLY BLADED GAS TURBINE ROTORS 审中-公开
标题翻译：的生产方法整体叶片的燃气涡轮转子的
公开(公告)号：WO2010003404A2
公开(公告)日：2010-01-14
申请号：PCT/DE2009000959
申请日：2009-07-09
申请人： MTU AERO ENGINES GMBH , KNOTT ULRICH , UIHLEIN THOMAS
发明人： KNOTT ULRICH , UIHLEIN THOMAS
IPC分类号： B23K20/12 , B23K20/24 , F01D5/30 , F01D5/34
CPC分类号： B23K20/129 , B23K20/24 , B23K2201/001 , B23P15/006 , F01D5/3061 , F05B2230/239
摘要： The invention relates to a method for producing integrally bladed gas turbine rotors. In said method, a blade ring composed of several blades is connected to a rotor base in such a way that a material is connected to the blade ring in order to fix the blade ring to said material by means of a friction welding process when the blade ring is connected to the rotor base, and the material is removed from the blade ring once the blade ring has been connected to the rotor base. According to the invention, the blade ring is connected to a plastic material in such a way that liquid plastic material is connected to the blade ring by means of an injection molding process. Alternatively, the blade ring is connected to a plastic material in such a way that at least one solid molded plastic piece is glued to the blade ring. Alternatively, the blade ring is connected to a metal foam in such a way that a separating means which prevents the metal foam from integrally bonding to the blade ring is placed between the metal foam and the blade ring. Alternatively, the blade ring is connected to a plastic material in such a way that solid plastic granulate is introduced into hollow spaces of the blade ring, whereupon the plastic granulate is fused and is connected to the blade ring.
摘要翻译：本发明涉及用于整体叶片燃气轮机转子的制造方法，与多个叶片中的一个叶片环连接到转子基体中，材料与叶片环的叶片环通过摩擦焊接到该材料固定其连接到转子基体连接的方式被移除，并且其中，所述叶片环连接到转子基体后，叶片环的材料。根据叶片环的本发明是连接到一个塑料，并且使得液体塑料通过注射成型与所述叶片环相连接。可替换地，叶片环与塑料相连接，在至少一个与所述叶片环固塑料成型件通过粘合连接这样的方式。可替换地，叶片环被连接到金属泡沫，以这样的方式，该金属泡沫和叶片环之间，脱模剂被定位，从而防止金属泡沫的与叶片环的材料连接。可替换地，叶片环与塑料连接，在固体塑料颗粒被引入到叶片环的空腔这样的方式，随后被熔化塑料颗粒并连接到叶片环上。

2. 发明申请

WO2010043210A8 METHOD FOR CONNECTING AT LEAST ONE TURBINE BLADE TO A TURBINE DISK OR A TURBINE RING 审中-公开
标题翻译：方法用于连接至少一个涡轮机叶片的涡轮机磁盘或涡轮环
公开(公告)号：WO2010043210A8
公开(公告)日：2011-05-12
申请号：PCT/DE2009001438
申请日：2009-10-16
申请人： MTU AERO ENGINES GMBH , UIHLEIN THOMAS , KOPPERGER BERTRAM , STEINHARDT ERICH
发明人： UIHLEIN THOMAS , KOPPERGER BERTRAM , STEINHARDT ERICH
IPC分类号： B23P15/00 , B23K13/01 , B23K15/00 , B23K26/20 , B23K35/00 , C23C24/04 , F01D5/30 , F01D5/34
CPC分类号： B23P15/006 , B23K13/01 , B23K15/0053 , B23K15/0093 , B23K26/24 , B23K26/32 , B23K31/02 , B23K35/3033 , B23K35/3046 , B23K35/325 , B23K2201/001 , B23K2203/08 , B23K2203/16 , B23K2203/26 , B23K2203/52 , C23C24/04 , F01D5/3061 , F05D2230/233 , F05D2230/234 , F05D2230/30 , Y10T29/49321
摘要： The invention relates to a method for connecting at least one turbine blade (10) to a turbine disk (18) or a turbine ring for a turbine stage of a turbomachine, particularly a thermal gas turbine, wherein first a connecting body (16) is produced on the at least one turbine blade (10) using a cold gas spraying method, and the connecting body (16) is subsequently connected to the turbine disk (18) or to the turbine ring using a fusion welding method. The invention further relates to a turbine stage for a turbine of a turbomachine and to a turbomachine having a turbine.
摘要翻译：本发明涉及一种用于一个连接体（16）连接具有一个涡轮机盘（18）或一种用于涡轮机的涡轮机级的涡轮机环的至少一个涡轮机叶片（10），尤其是热式气体涡轮机，其中，冷气体的第一装置喷涂法，到所述至少一个涡轮叶片（ 10形成）和连接体（16），然后（通过熔焊处理到涡轮盘18）或连接至所述涡轮机环。本发明还涉及一种涡轮机的涡轮机，并与涡轮机的流机的涡轮机级。

3. 发明申请

WO2008003295A3 METHOD FOR REPAIRING AND/OR REPLACING INDIVIDUAL ELEMENTS OF A GAS TURBINE COMPONENT 审中-公开
标题翻译：用于修理和/或更换汽轮机组件的单个元件的方法
公开(公告)号：WO2008003295A3
公开(公告)日：2008-04-03
申请号：PCT/DE2007001166
申请日：2007-06-30
申请人： MTU AERO ENGINES GMBH , EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS , GINDORF ALEXANDER
发明人： EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS , GINDORF ALEXANDER
IPC分类号： B23K13/01
CPC分类号： B23P6/005 , B23K13/015 , B23K2201/001 , B23K2201/34 , B23K2203/14 , F01D5/005 , F05D2230/232 , F05D2230/80 , F05D2230/90 , Y02T50/67 , Y10T29/49318
摘要： The invention relates to a method for repairing and/or replacing individual elements of a gas turbine component (10), particularly a blade or blade part arranged on a rotor support of a gas turbine, at least some of the components (10) being provided with at least one wear-resistant and/or erosion-resistant layer. The inventive method comprises the following steps: a) a coated or uncoated individual element that is damaged and/or needs to be replaced is removed from the component (10); b) a coated, partially coated, or uncoated replacement element (12) is provided; c) the replacement element (12) is fed and aligned relative to the component (10); and d) the replacement element (12) is connected to the component (10), corresponding contact areas (20, 22) of the replacement element (12) and the component (10) being connected by means of an inductive low-frequency or high-frequency pressure welding process.
摘要翻译：本发明涉及用于修复和/或更换一个燃气涡轮机的部件（10）的单独的元件的方法，特别是用于修复和/或更换一个，布置在气体涡轮机叶片的转子的载体或翼型件的一部分，其中，所述上部件（10）至少部分地具有至少一个磨损和/或侵蚀保护层，并且该方法包括以下步骤：a）分离部件（10）的损坏和/或交换的涂覆或未涂覆的单个元件; b）提供涂覆的，部分涂覆的或未涂覆的替换元件（12）; c）将替换元件（12）相对于部件（10）进给和对准; 和d）更换元件（12）与所述部件（10），其中，所述置换单元（12）和通过电感的低或高频压力焊接手段的部件（10）的连接对应的连接表面（20，22）进行连接。

4. 发明申请

WO2009138062A3 PROTECTIVE LAYER AND METHOD FOR APPLYING A PROTECTIVE LAYER 审中-公开
标题翻译：保护涂层方法施加保护层
公开(公告)号：WO2009138062A3
公开(公告)日：2010-03-18
申请号：PCT/DE2009000651
申请日：2009-05-12
申请人： MTU AERO ENGINES GMBH , EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS
发明人： EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS
IPC分类号： C23C14/04
CPC分类号： C23C14/04 , F01D5/288 , F05D2230/90
摘要： The invention relates to a method for applying a protective layer (100) to a predetermined area of a component (102) by physical gas deposition. Said method comprises a step wherein a component (102) is provided and another step of carrying out the physical gas deposition. Said physical gas deposition is carried out in such a manner that during said process, the predetermined area is arranged opposite a target (104) for a longer period of time than another area of the component (102).
摘要翻译：本发明涉及一种用于通过物理气相沉积来涂覆保护层（100）的组件（102）的预定范围内的方法。该方法包括将组件（102）并进行物理气相沉积的步骤Bereitsteilens的步骤。使得所述预定区域时，物理气相沉积（104）在被设置相对一个目标在一个较长时期，比组件（102）的另外的区域中的物理气相沉积进行。

5. 发明申请

WO2009049597A2 WEAR PROTECTION COATING 审中-公开
标题翻译：穿戴防护涂料
公开(公告)号：WO2009049597A2
公开(公告)日：2009-04-23
申请号：PCT/DE2008001668
申请日：2008-10-10
申请人： MTU AERO ENGINES GMBH , EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS
发明人： EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS
IPC分类号： C23C28/00
CPC分类号： C23C28/00 , C23C28/322 , C23C28/34 , C23C28/345 , C23C28/347 , Y10T428/24364
摘要： The invention relates to a wear protection coating (10), particularly erosion protection coating, which is applied to a surface (11) to be protected of a component (12) subject to fluid mechanics stress, particularly a gas turbine component. According to the invention, an outer layer is configured as a smoothing layer (13), which compensates for unevenness or roughness and/or imperfections of the wear protection coating.
摘要翻译：本发明涉及一种耐磨涂层（10），特别是耐侵蚀性涂层的表面上，以被保护（11）的流体强调部件（12），特别是燃气涡轮机部件，被施加。根据本发明的外层作为平滑层（13）形成，这在耐磨涂层的不平整补偿或粗糙度和/或缺陷。

6. 发明申请

WO2012025090A2 CLEANING OF A TURBO-MACHINE STAGE 审中-公开
标题翻译：清洗TURBOMASCHINEN STAGE
公开(公告)号：WO2012025090A2
公开(公告)日：2012-03-01
申请号：PCT/DE2011001545
申请日：2011-08-03
申请人： MTU AERO ENGINES GMBH , ROESING JUERGEN , SEIDEL FRANK , WINKLER LUTZ , KRIEGL BERND , UIHLEIN THOMAS , DUERR MARTIN , MORITZ FABIAN
发明人： ROESING JUERGEN , SEIDEL FRANK , WINKLER LUTZ , KRIEGL BERND , UIHLEIN THOMAS , DUERR MARTIN , MORITZ FABIAN
CPC分类号： B24C1/003 , B08B7/0021 , B08B9/00 , B24C1/086 , B24C3/325 , F01D25/002
摘要： The invention relates to a method for cleaning a turbo-machine stage (100) consisting of at least one of the following steps: a cleaning nozzle (1) is introduced into an opening of a turbo-machine, in particular into an inspection opening (220); and the blade (100) of the stage is acted upon by solid particles, said particles subliming at the blade temperature, in particular into dry ice particles.
摘要翻译：根据本发明包括用于清洁涡轮机级（100）的所述步骤中的至少一种的方法：将通过一个涡轮机的开口的清洗喷嘴（1），特别是通过检查开口（220）; 并且暴露步骤通过用干冰颗粒升华在叶片温度，特别是固体颗粒的刀片（100）。

7. 发明申请

WO2008154890A3 ANTI-WEAR COATING AND COMPONENT COMPRISING AN ANTI-WEAR COATING 审中-公开
标题翻译：磨损保护涂层和组件与磨损保护涂层
公开(公告)号：WO2008154890A3
公开(公告)日：2009-06-18
申请号：PCT/DE2008000841
申请日：2008-05-17
申请人： MTU AERO ENGINES GMBH , EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS
发明人： EICHMANN WOLFGANG , HEUTLING FALKO , UIHLEIN THOMAS
IPC分类号： C23C28/00 , F01D5/28
CPC分类号： C23C28/321 , C23C28/322 , C23C28/34 , C23C28/347 , C23C28/36 , C23C28/42 , F01D5/288 , Y10T428/12535 , Y10T428/12549 , Y10T428/31678
摘要： The invention relates to an anti-wear coating, in particular an anti-erosion coating, which is applied to the surface of a component to be protected that is used in flow technology, in particular a gas turbine component. According to the invention, the anti-wear coating is formed by one or several multi-layer system(s) applied in succession to the surface to be coated and the or each multi-layer system comprises at least one relatively soft metallic layer and at least one relatively hard ceramic layer. According to the invention, all layers of the or each multi-layer system are chromium-based and a diffusion barrier layer with a mono-nanostructure is applied to the multi-layer system or systems.
摘要翻译：本发明涉及一种耐磨涂层，其中所述耐磨涂层由一个形成，或者在重复更加施加在表面上被涂覆多层涂层系统，其被施加到表面以被保护的流体的强调成分，特别是气体涡轮机部件特别耐侵蚀性涂层，并且其中，所述包含或每个多层涂层系统包括至少一个相对较软的，金属层和至少一个相对坚硬，陶瓷层。根据本发明，被保护的所有层或上的铬基每个多层涂层的系统，所述表面之间和/多层涂层系统（一个或多个）的单纳米结构化扩散阻挡层施加。

8. 发明申请

WO2005066384A8 WEAR-RESISTANT LAYER AND COMPONENT COMPRISING A WEAR-RESISTANT LAYER 审中-公开
标题翻译：磨损保护涂层和组件与磨损保护涂层
公开(公告)号：WO2005066384A8
公开(公告)日：2006-04-20
申请号：PCT/DE2004002800
申请日：2004-12-22
申请人： MTU AERO ENGINES GMBH , EICHMANN WOLFGANG , GERSTNER ROLF , MANIER KARL-HEINZ , UECKER MARKUS , UIHLEIN THOMAS
发明人： EICHMANN WOLFGANG , GERSTNER ROLF , MANIER KARL-HEINZ , UECKER MARKUS , UIHLEIN THOMAS
IPC分类号： C23C14/06 , C23C28/00 , C23C30/00
CPC分类号： F01D5/288 , C23C28/321 , C23C28/322 , C23C28/34 , C23C28/347 , C23C28/36 , C23C28/42 , F01D5/286 , F05D2230/313 , F05D2230/90 , F05D2300/611 , Y10T428/12542 , Y10T428/12576
摘要： The invention relates to a wear-resistant layer, in particular an erosion resistant layer, for a fludically stressed component. According to the invention, the wear-resistant layer comprises one or several multi-layer systems (15, 16) which are repeatedly applied to the surface which is to be coated. Each of the applied multi-layered systems (15, 16) comprises at least four different layers. A first layer (17), which is oriented towards the surface which is to be coated, of each multi-layered system is made of a metal material adapted to the composition of the surface of the component which is to be coated. A second layer (18), which is applied to the first layer of each multi-layered system, is made of a metal alloy material adapted to the composition of the surface of the component which is to be coated. A third layer (19), which is applied to the second layer of each multi-layered system, is made of graduated metal ceramic material and a fourth layer (20), which is applied to the third layer of each multi-layered system, is made of a nanostructured ceramic material.
摘要翻译：本发明涉及一种磨损保护涂层，特别是用于流体的耐侵蚀性涂层强调成分。根据本发明的Verschleisschutzbeschichtung一个或多个，在待涂覆的表面上重复施加多层涂层系统（15，16），其中，每个所施加的多层涂层系统（15，16）的具有至少四个不同的层。第一对置面的要被涂覆的每个多层系统的层（17）由一个匹配于部件表面的组合物形成待涂布的金属材料。施加到每个多层系统的第一层第二层（18）一种涂层由匹配于部件表面的所述组合物被涂布，金属合金材料形成。施加到每个多层系统的第二层第三层（19）一种涂层由梯度金属陶瓷材料制成，并且施加到每个多层系统的第三层第四层（20）的涂层是由纳米结构陶瓷材料形成。

9. 发明申请

WO2009006871A2 TURBOMACHINE BLADE 审中-公开
标题翻译： TURBOMASCHINEN铲
公开(公告)号：WO2009006871A2
公开(公告)日：2009-01-15
申请号：PCT/DE2008001042
申请日：2008-06-21
申请人： MTU AERO ENGINES GMBH , KRIEGL BERND , UIHLEIN THOMAS
发明人： KRIEGL BERND , UIHLEIN THOMAS
IPC分类号： F01D5/28
CPC分类号： F01D5/288 , C23C4/06 , C23C28/044 , F05D2230/31 , F05D2230/90 , F05D2300/226 , F05D2300/2262 , Y02T50/673
摘要： The invention relates to a turbomachine blade (10), in particular a gas-turbine blade, having a blade aerofoil (11) which has a flow leading edge (13) and a flow trailing edge (14), with a suction side and pressure side of the blade aerofoil extending between the flow leading edge and the flow trailing edge. According to the invention, the blade aerofoil (11) is coated at least in the area of the flow leading edge (13) with a ductile wear-protection layer, with the ductile wear-protection layer having ceramic hard particles incorporated in a metal matrix.
摘要翻译：本发明涉及一种涡轮机叶片（10），特别是燃气涡轮机叶片，具有流动进入棱边（13）和具有叶片（11）的流出口边缘（14），其中，存在延伸流动前缘和流动后缘之间的翼型件的吸力侧和压力侧。根据本发明，所述叶片（11）是至少在与延性磨损保护层涂层的流动前缘（13）的区域中，其特征在于，在金属基体具有嵌入陶瓷的硬质颗粒的延性磨损保护层。

10. 发明申请

WO2012055881A3 ANTI-WEAR COATING 审中-公开
标题翻译：穿戴防护涂料
公开(公告)号：WO2012055881A3
公开(公告)日：2012-10-04
申请号：PCT/EP2011068678
申请日：2011-10-25
申请人： MTU AERO ENGINES GMBH , UIHLEIN THOMAS , EICHMANN WOLFGANG , HEUTLING FALKO , BRENDEL ANNEGRET
发明人： UIHLEIN THOMAS , EICHMANN WOLFGANG , HEUTLING FALKO , BRENDEL ANNEGRET
IPC分类号： C23C28/04 , C23C14/22 , F01D5/28
CPC分类号： B32B7/02 , B32B2250/42 , C04B2237/04 , C04B2237/086 , C04B2237/363 , C04B2237/597 , C23C28/042 , C23C28/044 , C23C28/40 , F01D5/288 , F05D2230/313 , F05D2300/611 , Y10T428/24149
摘要： The invention relates to an anti-wear coating, specifically for components which are subject to erosion under mechanical loading, in particular for gas turbine components, said coating comprising at least two different individual layers which preferably alternate with one another multiply and are applied to a surface of a component which is to be coated. The individual layers comprise a ceramic main layer (45, 46, 47, 48) and a quasi-ductile, non-metallic intermediate layer (41, 42, 43, 44).
摘要翻译：本发明涉及一种耐磨涂层，特别是对在机械应力下包含至少两个不同的，优选每反复交替，施加到待涂覆表面的部件各个层的侵蚀加载的组件，特别是用于燃气涡轮机组件。各个层包括主陶瓷层（45，46，47，48）和一个准韧性，非金属中间层（41，42，43，44）。

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