-
31.发明申请METHOD FOR CONNECTING AT LEAST ONE TURBINE BLADE TO A TURBINE DISK OR A TURBINE RING 审中-公开将至少一个涡轮叶片连接到涡轮盘或涡轮环的方法公开(公告)号：US20110217176A1
公开(公告)日：2011-09-08
申请号：US13122920
申请日：2009-10-16
CPC分类号： B23P15/006 , B23K13/01 , B23K15/0053 , B23K15/0093 , B23K26/24 , B23K26/32 , B23K31/02 , B23K35/3033 , B23K35/3046 , B23K35/325 , B23K2101/001 , B23K2103/08 , B23K2103/16 , B23K2103/26 , B23K2103/52 , 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 formed on the at least one turbine blade (10) by means of a cold gas spraying method, and the connecting body (16) is subsequently connected to turbine disk (18) or to the turbine ring by means of a fusion-welding method. The invention further relates to a turbine stage for a turbine of a turbomachine as well as a turbomachine having a turbine.
摘要翻译： 本发明涉及一种用于将至少一个涡轮叶片（10）连接到涡轮机（涡轮机）的涡轮机叶轮（18）或用于涡轮机（特别是热燃气涡轮机）的涡轮机级的涡轮机的方法，其中首先将连接体（16） 通过冷气喷射方法在所述至少一个涡轮叶片（10）上形成，并且所述连接体（16）随后通过熔焊方法连接到涡轮盘（18）或连接到所述涡轮环。 本发明还涉及一种用于涡轮机的涡轮机的涡轮级以及具有涡轮机的涡轮机。
-
32.发明授权公开(公告)号：US09114480B2
公开(公告)日：2015-08-25
申请号：US13056022
申请日：2009-08-06
申请人： Ulrich Knott , Erwin Bayer , Thomas Uihlein
发明人： Ulrich Knott , Erwin Bayer , Thomas Uihlein
IPC分类号： B23K20/12 , F01D5/30 , B23K1/00 , B23K13/01 , B23K20/16 , B23K20/22 , C30B29/52 , C30B33/06 , F01D5/34
CPC分类号： B23K20/12 , B23K1/0018 , B23K13/01 , B23K20/1205 , B23K20/1215 , B23K20/129 , B23K20/16 , B23K20/22 , B23K2101/001 , C30B29/52 , C30B33/06 , F01D5/3061 , F01D5/34 , F05B2230/239 , F05D2300/607
摘要： The present invention relates to methods for joining a rotationally asymmetrical part, preferably a turbine blade, which is made of a monocrystalline material, to a part, preferably a rotor core, which is made of polycrystalline material, having the method steps of: —joining the rotationally asymmetrical part to an adapter piece made of polycrystalline material by means of rotational friction welding, and —joining the adapter piece to the part made of polycrystalline material. The present invention also relates to a turbine blisk having a rotor core made of polycrystalline material and turbine blades made of monocrystalline material.
摘要翻译： 本发明涉及用于将由单晶材料制成的旋转非对称部分（优选为涡轮叶片）接合到由多晶材料制成的部分，优选为转子芯的方法，所述方法包括以下步骤： - 连接 通过旋转摩擦焊接到由多晶材料制成的适配件的旋转不对称部分，并将适配件连接到由多晶材料制成的部件上。 本发明还涉及具有由多晶材料制成的转子芯和由单晶材料制成的涡轮叶片的涡轮叶片。
-
33.发明申请公开(公告)号：US20110129353A1
公开(公告)日：2011-06-02
申请号：US13056022
申请日：2009-08-06
申请人： Ulrich Knott , Erwin Bayer , Thomas Uihlein
发明人： Ulrich Knott , Erwin Bayer , Thomas Uihlein
CPC分类号： B23K20/12 , B23K1/0018 , B23K13/01 , B23K20/1205 , B23K20/1215 , B23K20/129 , B23K20/16 , B23K20/22 , B23K2101/001 , C30B29/52 , C30B33/06 , F01D5/3061 , F01D5/34 , F05B2230/239 , F05D2300/607
摘要： The present invention relates to methods for joining a rotationally asymmetrical part, preferably a turbine blade, which is made of a monocrystalline material, to a part, preferably a rotor core, which is made of polycrystalline material, having the method steps of:—joining the rotationally asymmetrical part to an adapter piece made of polycrystalline material by means of rotational friction welding, and—joining the adapter piece to the part made of polycrystalline material. The present invention also relates to a turbine blisk having a rotor core made of polycrystalline material and turbine blades made of monocrystalline material.
摘要翻译： 本发明涉及用于将由单晶材料制成的旋转非对称部分（优选为涡轮叶片）接合到由多晶材料制成的部分，优选为转子芯的方法，所述方法包括以下步骤： - 连接 通过旋转摩擦焊接到由多晶材料制成的接头片的旋转不对称部分，以及将接合件连接到由多晶材料制成的部件上。 本发明还涉及具有由多晶材料制成的转子芯和由单晶材料制成的涡轮叶片的涡轮叶片。
-
公开(公告)号：US20090233111A1
公开(公告)日：2009-09-17
申请号：US11989374
申请日：2006-08-04
申请人： Thomas Uihlein
发明人： Thomas Uihlein
CPC分类号： F01D5/288 , C23C4/11 , C23C28/042 , C23C28/044 , C23C28/42 , C23C30/00 , F05D2230/90 , F05D2300/2118 , F05D2300/611 , F05D2300/612 , Y02T50/67 , Y02T50/672 , Y02T50/6765
摘要： The invention relates to a thermal insulation layer system (11) for structural components (10), in particular for metallic structural components of a gas turbine such as an aircraft engine, wherein the thermal insulation layer system (11) is formed of a thermal insulation base material. According to the invention, at least one aerogel is incorporated or encased or embedded in the thermal insulation base material.
摘要翻译： 本发明涉及一种用于结构部件（10）的隔热层系统（11），特别是用于诸如飞机发动机的燃气轮机的金属结构部件，其中绝热层系统（11）由绝热层 基材。 根据本发明，至少一种气凝胶结合或包裹或嵌入在绝热基材中。
-
35.发明授权Strip coatings for metal components of drive units and their process of manufacture 失效驱动单元金属部件的带状涂层及其制造工艺公开(公告)号：US06171351B2
公开(公告)日：2001-01-09
申请号：US08937581
申请日：1997-09-25
申请人： Johannes Schröder , Thomas Uihlein , Hans Weber , Herbert Fischer , Erwin Fischhaber , Norbert Legrand
发明人： Johannes Schröder , Thomas Uihlein , Hans Weber , Herbert Fischer , Erwin Fischhaber , Norbert Legrand
IPC分类号： B24B100
CPC分类号： F01D11/12 , C23C4/01 , F01D5/20 , F05D2230/90 , F05D2300/21 , Y10T428/24413 , Y10T428/24926 , Y10T428/256 , Y10T428/257
摘要： An abrasive coating is formed on the tip of a component of a drive unit for abrading an abradable coating during a stripping operation by thermal spraying a ceramic layer on the component, the ceramic layer being profiled and providing a succession of abrading edges and intermediate spaces between the abrading edges to take up and remove abraded material. The abrading edges can be formed as deposits of ceramic material on the component or, as a ceramic layer applied on a profiled surface etched on the component.
摘要翻译： 在驱动单元的部件的尖端上形成研磨涂层，用于在剥离操作期间通过在组件上热喷涂陶瓷层，陶瓷层被成型并提供一系列研磨边缘和中间间隔 研磨边缘用于吸收和去除磨损的材料。 研磨边缘可以形成为陶瓷材料在部件上的沉积物，或者作为施加在蚀刻在部件上的异型表面上的陶瓷层。
-
36.发明授权Strip coatings for metal components of drive units and their process of manufacture 失效驱动单元金属部件的带状涂层及其制造工艺
公开(公告)号：US5756217A
公开(公告)日：1998-05-26
申请号：US529274
申请日：1995-09-15
申请人： Johannes Schroder , Thomas Uihlein , Hans Weber , Herbert Fischer , Erwin Fischhaber , Norbert Legrand
发明人： Johannes Schroder , Thomas Uihlein , Hans Weber , Herbert Fischer , Erwin Fischhaber , Norbert Legrand
CPC分类号： F01D11/12 , C23C4/01 , F01D5/20 , F05D2230/90 , F05D2300/21 , Y10T428/24413 , Y10T428/24926 , Y10T428/256 , Y10T428/257
摘要： An abrasive coating is formed on the tip of a component of a drive unit for abrading an abradable coating during a stripping operation by thermal spraying a ceramic layer on the component, the ceramic layer being profiled and providing a succession of abrading edges and intermediate spaces between the abrading edges to take up and remove abraded material. The abrading edges can be formed as deposits of ceramic material on the component or, as a ceramic layer applied on a profiled surface etched on the component.
摘要翻译： 在驱动单元的部件的尖端上形成研磨涂层，用于在剥离操作期间通过在组件上热喷涂陶瓷层，陶瓷层被成型并提供一系列研磨边缘和中间间隔 研磨边缘用于吸收和去除磨损的材料。 研磨边缘可以形成为陶瓷材料在部件上的沉积物，或者作为施加在蚀刻在部件上的异型表面上的陶瓷层。
-
37.发明授权
公开(公告)号：US5087512A
公开(公告)日：1992-02-11
申请号：US625747
申请日：1990-12-11
申请人： Thomas Uihlein , Gerhard Wydra
发明人： Thomas Uihlein , Gerhard Wydra
CPC分类号： C23C30/00 , Y02T50/67 , Y10T428/12389 , Y10T428/12604 , Y10T428/12611 , Y10T428/24702 , Y10T428/249928 , Y10T428/256 , Y10T442/3415
摘要： A structural component of metal is protected against titanium fires that can be caused by flying and burning titanium droplets, e.g. in a propulsion unit. The protection against titanium fires of metal structural components is provided by a surface coating made of ceramic fibers embedded in a matrix material of a high temperature lacquer having dispersed therein aluminum powder as a filler material. The high temperature resistant lacquer is formed of silicates as a vehicle in which the aluminum powder is dispersed.
摘要翻译： 金属的结构部件可以防止钛火焰的飞溅和燃烧引起钛火焰， 在推进单位。 金属结构部件的钛火焰的保护是通过嵌入在其中分散有铝粉末作为填充材料的高温漆的基质材料中的陶瓷纤维制成的表面涂层来提供的。 耐高温漆由作为其中分散有铝粉末的载体的硅酸盐形成。
-
公开(公告)号：US09492906B2
公开(公告)日：2016-11-15
申请号：US13813919
申请日：2011-08-03
申请人： Jürgen Rösing , Frank Seidel , Lutz Winkler , Bernd Kriegl , Thomas Uihlein , Martin Dürr , Fabian Moritz
发明人： Jürgen Rösing , Frank Seidel , Lutz Winkler , Bernd Kriegl , Thomas Uihlein , Martin Dürr , Fabian Moritz
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： 本发明涉及一种用于清洁由以下至少一个步骤组成的涡轮机台（100）的方法：将清洁喷嘴（1）引入涡轮机的开口中，特别是引入到检查开口 220）; 并且所述台的叶片（100）由固体颗粒作用，所述颗粒在叶片温度下升华，特别是干冰颗粒。
-
公开(公告)号：US08936442B2
公开(公告)日：2015-01-20
申请号：US12998977
申请日：2010-01-30
申请人： Thomas Uihlein , Erich Steinhardt
发明人： Thomas Uihlein , Erich Steinhardt
IPC分类号： F01D5/14 , F04D29/38 , B23K15/00 , B23K26/20 , B23K35/30 , F01D5/34 , B23K26/32 , B23K26/34 , B23K35/02
CPC分类号： B23K15/0053 , B23K15/0086 , B23K26/211 , B23K26/32 , B23K26/342 , B23K35/0238 , B23K35/3033 , B23K2101/001 , B23K2103/18 , B23K2103/26 , F01D5/34 , F05D2230/22 , F05D2230/233 , F05D2230/234 , F05D2250/232 , Y10T29/49316
摘要： A method for manufacturing an integrally bladed rotor (10), in particular for a gas turbine, including the following method steps: preparing a rotor base member (12) having at least one first weld surface (16) and one blade (14) having a second weld surface (18); positioning the rotor base member (12) and the blade (14) in such a way that a join zone (20) is formed between the first and second weld surface (16, 18); and filling the join zone (20) with metal powder (24) and the laser welding or electron beam welding of the metal powder (24). An integrally bladed rotor (10) has a join zone (20) between the rotor base member (12) and blades (14), the join zone (20) being filled with welded metal powder (24).
摘要翻译： 一种用于制造整体叶片的转子（10）的方法，特别是用于燃气轮机的方法，包括以下方法步骤：制备具有至少一个第一焊接表面（16）和一个叶片（14）的转子基体部件（12） 第二焊接表面（18）; 将转子基部构件（12）和叶片（14）定位成使得在第一和第二焊接表面（16,18）之间形成接合区域（20）; 以及用金属粉末（24）填充接合区域（20）以及金属粉末（24）的激光焊接或电子束焊接。 一体式叶片式转子（10）在转子基部构件（12）和叶片（14）之间具有接合区域（20），接合区域（20）填充有焊接的金属粉末（24）。
-
公开(公告)号：US08153274B2
公开(公告)日：2012-04-10
申请号：US12304978
申请日：2007-06-12
CPC分类号： C23C28/3215 , C23C28/322 , C23C28/325 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/90 , F05D2300/21 , F05D2300/2112 , F16L59/029 , Y02T50/67 , Y02T50/672 , Y10T428/12549 , Y10T428/12611 , Y10T428/12618 , Y10T428/26
摘要： A thermal barrier layer for metallic components, in particular for gas turbine components which are subject to high temperatures or hot gas, is disclosed. The thermal barrier layer includes an inner contact layer and an outer top layer, where the inner contact layer is applied to a surface of the component via an adhesion-promoting layer that is disposed therebetween, and between the outer top layer and the inner contact layer an intermediate layer is formed.
摘要翻译： 公开了用于金属部件的热障层，特别是用于经受高温或热气体的燃气轮机部件。 隔热层包括内接触层和外顶层，其中内接触层经由设置在其间的粘合促进层，以及在外顶层和内接触层之间施加到部件的表面 形成中间层。
-
-
-
-
-
-
-
-
-
搜索结果
44 条记录 (耗时 0.034 秒)
