公开(公告)号：US10012097B2

公开(公告)日：2018-07-03

申请号：US14767183

申请日：2014-02-19

申请人： Snecma

发明人： Sébastien Jean Laurent Prestel ,  Denis Aydin ,  Rémi Blanc ,  Hélène Condat ,  Patrice Jean-Marc Rosset

IPC分类号： F01D9/04 ,  F01D25/24 ,  F01D11/00

CPC分类号： F01D9/04 ,  F01D9/042 ,  F01D11/005 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/323 ,  F05D2230/18 ,  F05D2230/238 ,  F05D2230/60 ,  F05D2230/644 ,  F05D2240/125

摘要： A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

公开(公告)号：US09770758B2

公开(公告)日：2017-09-26

申请号：US15219921

申请日：2016-07-26

申请人： United Technologies Corporation

发明人： JinQuan Xu

IPC分类号： B22D23/06 ,  B22D27/04 ,  B33Y10/00 ,  B33Y40/00 ,  B33Y80/00 ,  B22C9/10 ,  B22C9/22 ,  B22D29/00 ,  B22D25/02 ,  B22F3/105 ,  B22F3/24 ,  B22F5/04 ,  B23K15/00 ,  B23K26/342 ,  B23K26/70 ,  B23K37/00 ,  F01D5/00 ,  F01D5/12 ,  F01D9/04 ,  F02C7/22 ,  F23R3/00 ,  B23K101/00

CPC分类号： B22D27/045 ,  B22C9/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/108 ,  B22C9/12 ,  B22C9/22 ,  B22D23/06 ,  B22D25/02 ,  B22D29/001 ,  B22F3/1055 ,  B22F3/24 ,  B22F5/007 ,  B22F5/009 ,  B22F5/04 ,  B22F2003/248 ,  B22F2998/10 ,  B23K1/0018 ,  B23K9/04 ,  B23K9/167 ,  B23K15/0046 ,  B23K15/0086 ,  B23K20/00 ,  B23K26/34 ,  B23K26/342 ,  B23K26/70 ,  B23K31/02 ,  B23K37/00 ,  B23K2101/001 ,  B23P6/005 ,  B23P6/007 ,  B23P6/045 ,  B33Y10/00 ,  B33Y40/00 ,  B33Y80/00 ,  C30B11/00 ,  C30B11/003 ,  C30B21/02 ,  C30B29/52 ,  F01D5/005 ,  F01D5/12 ,  F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D9/04 ,  F02C7/222 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/233 ,  F05D2230/234 ,  F05D2230/235 ,  F05D2230/238 ,  F05D2230/30 ,  F05D2230/80 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2300/175 ,  F05D2300/20 ,  F05D2300/606 ,  F05D2300/608 ,  F23R3/002 ,  Y02P10/292 ,  Y02P10/295

摘要： A method of manufacturing a replacement body for a component is provided. The method includes the steps of: a) additively manufacturing a crucible for casting of the replacement body; b) solidifying a metal material within the crucible to form a directionally solidified microstructure within the replacement body; and c) removing the crucible to reveal the directionally solidified replacement body.

公开(公告)号：US20170266745A1

公开(公告)日：2017-09-21

申请号：US15459104

申请日：2017-03-15

申请人： MTU Aero Engines AG

发明人： Karl-Hermann RICHTER

IPC分类号： B23K1/18 ,  B23K1/002 ,  F01D25/04 ,  B23K1/008 ,  B23K1/20 ,  B23K1/00 ,  B23K1/005

CPC分类号： B23K1/18 ,  B23K1/0018 ,  B23K1/002 ,  B23K1/0056 ,  B23K1/008 ,  B23K1/206 ,  B23K2101/001 ,  B23K2101/12 ,  F01D5/14 ,  F01D5/16 ,  F01D9/041 ,  F01D25/04 ,  F04D29/666 ,  F05D2230/12 ,  F05D2230/237 ,  F05D2230/238 ,  F05D2260/30 ,  F05D2260/96 ,  F05D2260/961

摘要： The invention relates to a method for producing a mistuning component. The method comprises the following steps: a) producing a container (34) having at least one chamber (36); b) producing a lid (32, 32′); c) inserting at least one impulse element into the chamber (36); d) joining the lid (32, 32′) and the container (36), wherein joining is carried out by soldering/brazing.

公开(公告)号：US20170145849A1

公开(公告)日：2017-05-25

申请号：US15320708

申请日：2015-06-15

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Thomas Guillaume MONGIS ,  Guillame Benoit Noel CHAMPION ,  Pascal Jean-Serge DROUARD

IPC分类号： F01D11/12 ,  F01D9/04

CPC分类号： F01D11/122 ,  F01D9/041 ,  F01D11/001 ,  F01D21/003 ,  F04D29/164 ,  F04D29/542 ,  F04D29/644 ,  F05D2220/30 ,  F05D2230/237 ,  F05D2230/238 ,  F05D2230/644 ,  F05D2230/80

摘要： Method for repairing a turbine-engine component, such as a turbine nozzle (D), this component comprising an annular wall for supporting an abradable ring (C2), the method comprising first-repair steps (I) consisting in: removing a first abradable ring (C2), the brazing for fixing the ring to the annular wall, and an inner peripheral part of the annular wall, and fixing a second abradable ring (C2) to the annular wall by brazing, characterised in that the second abradable ring has finished dimensions (r1′), the first repair not having a step of grinding of the second ring after fixing thereof to the annular wall.

公开(公告)号：US20160215651A1

公开(公告)日：2016-07-28

申请号：US14992279

申请日：2016-01-11

申请人： MTU Aero Engines AG

发明人： Andreas Hartung

IPC分类号： F01D25/04 ,  F04D29/66 ,  F04D29/56 ,  F01D9/04 ,  F01D17/14

CPC分类号： F01D25/04 ,  F01D5/16 ,  F01D5/26 ,  F01D9/041 ,  F01D17/14 ,  F01D17/162 ,  F04D27/0246 ,  F04D29/563 ,  F04D29/668 ,  F05D2220/323 ,  F05D2230/11 ,  F05D2230/12 ,  F05D2230/238 ,  F05D2240/12 ,  F05D2240/50 ,  F05D2260/96 ,  Y02T50/671

摘要： The present invention relates to an adjustable guide vane for a turbomachine, having a vane element (1) and a turning disk (2, 3), which has a first impact chamber (4), in which an impulse element (5) is arranged with play of movement.

摘要翻译： 本发明涉及一种用于涡轮机的可调节导向叶片，其具有叶片元件（1）和转动盘（2,3），其具有第一冲击室（4），其中布置有脉冲元件（5） 随着运动的发挥。

公开(公告)号：US20150050126A1

公开(公告)日：2015-02-19

申请号：US14380480

申请日：2013-02-21

申请人： BorgWarner Inc.

发明人： Michael Loewenberg

IPC分类号： F04D29/054

CPC分类号： F04D29/054 ,  F01D5/025 ,  F05D2220/40 ,  F05D2230/232 ,  F05D2230/238 ,  F05D2300/174

摘要： An exhaust-gas turbocharger (1) having a shaft (2), which has a first centric bore (4) on an end face (3), a turbine wheel (5), which has a second centric bore (7) in the wheel rear side (6) thereof, a connection piece (8), which engages into the first and second bores (4, 7); and an integral connection device (9) for connecting the shaft (2) to the turbine wheel (5), wherein the connection piece (8) is hollow in form.

摘要翻译： 具有轴（2）的排气涡轮增压器（1），其在端面（3）上具有第一中心孔（4），涡轮机叶轮（5），其具有第二中心孔（7） 车轮后侧（6），连接件（8），其接合到第一和第二孔（4,7）中; 以及用于将所述轴（2）连接到所述涡轮机叶轮（5）的整体连接装置（9），其中所述连接件（8）的形状是中空的。

公开(公告)号：US08267659B2

公开(公告)日：2012-09-18

申请号：US12525156

申请日：2008-01-14

申请人： Fathi Ahmad ,  Scarlett Fajardo-Reina ,  Markus Gill ,  Stefan Werner Kiliani ,  Silvio-Ulrich Martin ,  Ralf Müsgen ,  Oliver Schneider

发明人： Fathi Ahmad ,  Scarlett Fajardo-Reina ,  Markus Gill ,  Stefan Werner Kiliani ,  Silvio-Ulrich Martin ,  Ralf Müsgen ,  Oliver Schneider

IPC分类号： F01D5/18

CPC分类号： F01D5/181 ,  F01D5/182 ,  F05D2230/237 ,  F05D2230/238 ,  F05D2240/241 ,  Y10T29/49341

摘要： A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure.

摘要翻译： 提供涡轮叶片。 涡轮机叶片包括支撑结构和壳体，其围绕支撑结构并且通过至少一个间隔元件连接到并且与支撑结构一定距离。 例如，间隔元件可以是焊球，以便形成冷却介质可以在支撑结构和壳体之间流动的空间。 还提供了一种用于生产具有支撑结构和壳体的涡轮叶片的方法，所述支撑结构和壳体围绕所述支撑结构并且连接到所述支撑结构并且距离所述支撑结构一定距离。 壳体至少在支撑结构的一个位置被焊接到支撑结构，以便将壳体与支撑结构连接并且与支撑结构相距一定距离。

公开(公告)号：US20090263239A1

公开(公告)日：2009-10-22

申请号：US11578862

申请日：2005-02-28

申请人： Manfred A. Daeubler ,  Horst Mueller-Wittek ,  Renate Mendritzki ,  Ulrike Hain ,  Werner Humhauser

发明人： Manfred A. Daeubler ,  Horst Mueller-Wittek ,  Renate Mendritzki ,  Ulrike Hain ,  Werner Humhauser

IPC分类号： F04D29/52

CPC分类号： F01D11/122 ,  F01D11/127 ,  F05D2230/236 ,  F05D2230/237 ,  F05D2230/238 ,  F05D2250/283 ,  F05D2300/601

摘要： A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.

摘要翻译： 提供了一种具有金属设计的环形结构，用于轴向流过压缩机和涡轮级的动叶片，特别是在燃气涡轮发动机中。 环形结构包括圆形环形外壁，圆形环形内壁，其位于距活动叶片尖端短的径向距离处，并且包括以中空室结构的形式设置在外部的外部的接合结构 墙壁和内壁。 外壁以压缩机或涡轮机台的封闭的，机械稳定的壳体壁的形式提供，并且以中空室结构的形式提供的接合结构以固定的方式连接到外壁和内壁 例如，通过焊接，扩散焊接或其它接合技术。 内壁以闭合的，机械稳定的结构的形式提供，其用作活动叶片尖端的穿入衬里，并且由金属织物和/或金属毡制成。

公开(公告)号：US20070157447A1

公开(公告)日：2007-07-12

申请号：US11650807

申请日：2007-01-08

申请人： Paul S. Prevey

发明人： Paul S. Prevey

IPC分类号： B23P6/00

CPC分类号： B23P9/04 ,  B23P6/002 ,  B23P9/00 ,  B23P9/02 ,  F01D5/005 ,  F05D2230/10 ,  F05D2230/232 ,  F05D2230/233 ,  F05D2230/237 ,  F05D2230/238 ,  F05D2230/30 ,  F05D2230/90 ,  Y02T50/673 ,  Y10T29/49718 ,  Y10T29/49764 ,  Y10T29/49771

摘要： A repaired component with improved material and mechanical properties and a method of improving the properties of a repaired component are provided. The repaired component comprises a body, a repaired area integral with the body, and an area of compressive residual stress wherein the area of compressive residual stress comprises at least a portion of the repaired area. One method for improving the fatigue performance, foreign object damage tolerance, and resistance to stress related failure mechanisms of a repaired component includes inducing a designed residual compressive stress distribution with a controlled amount of cold work in the repaired area to offset high-applied tensile stresses and stresses introduced as a result of the repair procedure as well as to improve the properties of the material added to the component during the repair.

摘要翻译： 提供了具有改进的材料和机械性能的修复的部件和改进修复部件的性质的方法。 被修复的部件包括主体，与主体一体的修复区域和压缩残余应力的区域，其中压缩残余应力的面积包括修复区域的至少一部分。 一种用于改善疲劳性能，异物损伤公差以及对被修复部件的应力相关破坏机理的抵抗力的一种方法包括在受修复的区域中引入设计的残余压应力分布与受控量的冷作业以抵消高应力拉应力 并且作为修复过程的结果引入的应力以及改善在修复期间添加到部件中的材料的性质。

公开(公告)号：US20180200806A1

公开(公告)日：2018-07-19

申请号：US15406947

申请日：2017-01-16

申请人： General Electric Company

发明人： Robert Edward Huth ,  Matthew Jason Clark

IPC分类号： B23B47/28 ,  B23Q9/00 ,  F02C3/04 ,  F02C3/14 ,  F02C7/22 ,  F04D29/52 ,  F04D29/64 ,  F01D25/28

CPC分类号： B23B47/28 ,  B23B2215/76 ,  B23P2700/13 ,  B23Q9/0042 ,  F01D5/025 ,  F01D5/026 ,  F01D21/04 ,  F01D21/045 ,  F01D21/06 ,  F01D21/10 ,  F01D21/14 ,  F01D25/285 ,  F02C3/04 ,  F02C3/14 ,  F02C6/12 ,  F02C7/22 ,  F04D29/522 ,  F04D29/644 ,  F05D2220/32 ,  F05D2220/40 ,  F05D2230/10 ,  F05D2230/14 ,  F05D2230/237 ,  F05D2230/238 ,  F05D2240/35 ,  F05D2260/311 ,  F23R2900/00018 ,  F23R2900/00019

摘要： A portable jig and fixture having at least one base plate, a column assembly removably coupled to the at least one base plate, a slide assembly removably coupled to the column assembly, a power feed head removably coupled to the slide assembly, and a spindle unit removably coupled with the slide assembly having a motor removably engaged it. At least one cutter assembly is removably engaged with the spindle unit and at least one drill jig is also removably engaged with the spindle unit. Also, a turbomachine having complementary structure on the compressor discharge casing can engage with the at least one base plate alignment mounting structure on the portable jig and fixture.