公开(公告)号：US20240352858A1

公开(公告)日：2024-10-24

申请号：US18736903

申请日：2024-06-07

申请人： SAFRAN AERO BOOSTERS

发明人： Yann Jean-Pierre Lefaux ,  Damiem VERHELST

IPC分类号： F01D5/02 ,  B23K20/12

CPC分类号： F01D5/02 ,  B23K20/129 ,  F05D2230/239

摘要： A method for sizing a section of a junction by orbital friction welding with an eccentric e, between a blade and a stub of a bladed disk for a turbomachine. The sized section has a rounded contour at one or two ends of said section along a chord of the blades, each corresponding to a leading edge or a trailing edge of said blades, said rounded contour(s) having over a sector of at least 120° an average radius of at least twice the eccentric e.

公开(公告)号：US20240253799A1

公开(公告)日：2024-08-01

申请号：US18405325

申请日：2024-01-05

申请人： Airbus Operations SAS

发明人： Anne-Laure LAFLY ,  Wolfgang BROCHARD

IPC分类号： B64D29/08 ,  F01D25/00

CPC分类号： B64D29/08 ,  F01D25/00 ,  F05D2230/239

摘要： An air inlet of a nacelle of an aircraft including a lip having a leading edge configured to split an air flow into interior and exterior air flows, the interior air flow entering the air inlet, an exterior panel, an intermediate panel, interposed between the lip and the exterior panel, having a first edge connected to the lip by at least a first connection and a second edge connected to the exterior panel by at least a second connection, the first connection connecting the first edge of the intermediate panel and the lip comprising at least one butt weld bead having an outer face in the extension of the outer faces of the lip and of the intermediate panel.

公开(公告)号：US20180209280A1

公开(公告)日：2018-07-26

申请号：US15877839

申请日：2018-01-23

申请人： ROLLS-ROYCE plc

发明人： John P E FORSDIKE ,  Simon E. BRAY ,  Gavin J. BAXTER ,  Andrew R. WALPOLE

IPC分类号： F01D5/30 ,  F01D5/02 ,  B23K20/12

CPC分类号： F01D5/3061 ,  B23K15/0086 ,  B23K15/0093 ,  B23K20/1205 ,  B23K20/129 ,  B23K20/16 ,  B23K20/233 ,  B23K20/24 ,  B23K26/0006 ,  B23K26/34 ,  B23K2101/001 ,  B23K2103/08 ,  B23K2103/26 ,  B33Y80/00 ,  F01D5/02 ,  F01D5/34 ,  F04D29/321 ,  F04D29/322 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/233 ,  F05D2230/239 ,  F05D2230/30 ,  F05D2300/175 ,  F05D2300/606

摘要： A method (56) for fabricating an integral assembly (24) is disclosed. The method comprises providing (56) a first workpiece (26) having a first surface and a second workpiece (30) having a second surface (54), performing a first bonding process between the first surface of the first workpiece (26) and the second surface (54) of the second workpiece (30) the bulk material of the first workpiece having a friction weld property that makes it more difficult to weld than a friction weld property at the surface.

公开(公告)号：US20170145837A1

公开(公告)日：2017-05-25

申请号：US15351797

申请日：2016-11-15

申请人： MTU Aero Engines AG

发明人： Martin SCHLOFFER ,  Wilfried SMARSLY

IPC分类号： F01D5/30

CPC分类号： F01D5/3061 ,  B23K20/1205 ,  B23K20/129 ,  B23K20/16 ,  B23K20/233 ,  B23K26/342 ,  B23K2101/001 ,  B23K2103/14 ,  B23K2103/18 ,  B23K2103/26 ,  F01D5/147 ,  F01D5/18 ,  F01D5/34 ,  F05D2220/323 ,  F05D2230/234 ,  F05D2230/236 ,  F05D2230/239 ,  F05D2230/31 ,  F05D2230/40 ,  F05D2230/42 ,  F05D2230/50 ,  F05D2300/174 ,  Y02T50/672

摘要： A method of making a bladed rotor for a turbomachine, in particular for an aircraft engine, is disclosed. The method comprises the steps a) providing a rotor base of the rotor, b) providing at least one blade root, c) providing at least one blade body, d) making at least one blade by connecting the blade body to the blade root by means of a diffusion barrier layer, at least the blade body, the diffusion barrier layer and the blade root consisting of respectively different materials, and e) joining the at least one blade root to the rotor base. The invention furthermore relates to a bladed rotor and to a turbomachine having such a bladed rotor.

公开(公告)号：US09656761B2

公开(公告)日：2017-05-23

申请号：US14266128

申请日：2014-04-30

申请人： The Boeing Company

发明人： Alex C. Lumbab ,  Bradley Scott Leisten

IPC分类号： F01D25/24 ,  B64D33/02 ,  B64C7/02 ,  F02C7/04

CPC分类号： B64D33/02 ,  B64C7/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/04 ,  F05D2230/239 ,  F05D2300/173 ,  Y02T50/671 ,  Y10T29/49828 ,  Y10T29/49909

摘要： A lipskin for a nacelle includes a generally annular first lipskin segment that extends generally upstream from a first lipskin edge to a forward edge. The forward edge is proximate to a hilite of the nacelle. The lipskin also includes a generally annular second lipskin segment that extends generally downstream from the forward edge to a second lipskin edge. The second lipskin segment is oriented generally concentrically about the first lipskin segment. The first lipskin segment and the second lipskin segment are coupled together at the forward edge.

公开(公告)号：US20160273074A1

公开(公告)日：2016-09-22

申请号：US15066186

申请日：2016-03-10

申请人： MTU Aero Engines AG

发明人： Wilfried SMARSLY ,  Markus FRIED

IPC分类号： C22C1/04 ,  B22F3/24 ,  B22F3/17 ,  C22C30/00 ,  B22F3/20 ,  B22F3/15 ,  B22F3/14 ,  C22C27/04 ,  B22F3/12 ,  B22F3/18

CPC分类号： C22C1/045 ,  B22F3/04 ,  B22F3/10 ,  B22F3/1039 ,  B22F3/12 ,  B22F3/14 ,  B22F3/15 ,  B22F3/17 ,  B22F3/18 ,  B22F3/20 ,  B22F3/24 ,  B22F5/04 ,  B22F2003/175 ,  B22F2301/20 ,  B22F2998/10 ,  B23K13/01 ,  B23K15/0093 ,  B23K20/02 ,  B23K20/12 ,  B23K20/22 ,  B23K26/21 ,  B23K26/323 ,  B23K2101/001 ,  B23K2103/18 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00 ,  C22C1/0491 ,  C22C27/04 ,  C22C30/00 ,  F01D5/282 ,  F01D5/286 ,  F01D5/288 ,  F05D2230/22 ,  F05D2230/233 ,  F05D2230/234 ,  F05D2230/236 ,  F05D2230/239 ,  F05D2230/25 ,  F05D2230/42 ,  F05D2300/13 ,  F05D2300/131 ,  F05D2300/172 ,  F05D2300/177 ,  F05D2300/222 ,  Y02T50/672 ,  Y02T50/6765

摘要： The present invention relates to a method for producing a component of a composite material comprising a metal matrix and incorporated intermetallic phases, which method comprises providing powders of at least one member of the group which comprises pure chemical elements, alloys, chemical compounds and material composites, the powder corresponding overall to the chemical composition which the composite material to be produced is intended to have, each individual powder being different to the chemical composition of the composite material to be produced, compacting the powders, bonding the powders to one another to form a unit and thermoplastically shaping the unit.

摘要翻译： 本发明涉及一种用于涡轮机的叶片，特别是用于飞行器发动机，其包括用于将叶片（1）布置在涡轮机中的叶根（2）和用于与流体流动相互作用的主叶片部分（3） 通过涡轮机，叶片根部和主叶片部分由不同的材料形成，主叶片部分由金属 - 金属间复合材料形成。 通过钼合金形成用于形成金属 - 金属间复合材料的金属间相的金属基体。 本发明还涉及用于生产这种叶片的相应方法。

公开(公告)号：US20160003140A1

公开(公告)日：2016-01-07

申请号：US14767848

申请日：2014-02-20

申请人： ECOMOTORS, INC.

发明人： Tyler GARRARD ,  Will Robert Nielson HIPPEN ,  Christopher Meszaros

IPC分类号： F02B39/10 ,  F02B33/34 ,  F01D25/16 ,  F01D5/02 ,  F01D15/10 ,  F01D25/24

CPC分类号： F02B39/10 ,  F01D5/02 ,  F01D15/10 ,  F01D25/16 ,  F01D25/166 ,  F01D25/24 ,  F02B33/34 ,  F02B37/04 ,  F02B39/00 ,  F05D2220/40 ,  F05D2230/233 ,  F05D2230/234 ,  F05D2230/235 ,  F05D2230/239 ,  F05D2230/60 ,  F05D2240/24 ,  Y02T10/144

摘要： By relieving the shaft of an electronically-controlled turbocharger (ECT) in a central region of where a rotor of an electric machine couples with the shaft eases assembly of the electric machine onto the shaft. On either side of the relieved section, the fit between the shaft and the rotor may be a slip fit or an interference fit. Alternatively, the rotor is relieved in a central section. In some embodiments, the shaft is welded to the rotor. In yet other embodiments, the outside of the shaft and the inside of the rotor are threaded with a nut or a pin to secure the shaft to the rotor or the rotor itself has threads to engage with threads on the shaft. Such arrangements ease assembly and allow adjustment of dynamic characteristics of the rotor system.

摘要翻译： 通过在电机的转子与轴耦合的中心区域中释放电子控制的涡轮增压器（ECT）的轴，将电机的组装简化为轴。 在卸载部分的两侧，轴和转子之间的配合可以是滑动配合或过盈配合。 或者，转子在中心部分被释放。 在一些实施例中，轴被焊接到转子。 在其它实施例中，轴的外侧和转子的内部都带有螺母或销，以将轴固定到转子上，或者转子本身具有与轴上的螺纹啮合的螺纹。 这种布置容易组装并允许调节转子系统的动态特性。

公开(公告)号：US20150308278A1

公开(公告)日：2015-10-29

申请号：US14693593

申请日：2015-04-22

申请人： Techspace Aero S.A.

发明人： Michel Wlasowski

IPC分类号： F01D9/04

CPC分类号： F01D9/044 ,  B23K20/1205 ,  B23K20/129 ,  B23K20/227 ,  B23K20/233 ,  B23K20/2333 ,  B23K2101/001 ,  B23K2103/04 ,  B23K2103/10 ,  B23K2103/14 ,  B23P15/006 ,  F05D2230/239 ,  F05D2230/53 ,  Y10T29/49323

摘要： The present application relates to a method for producing a housing for an axial turbomachine compressor having a metal sheet with annular rows of stator blades which are welded to the metal sheet. The method includes the steps of: (a) providing or producing a planar metal sheet with a step of machining in order to form blade stumps; (b) welding stator blades by means of friction to one of the planar faces of the metal sheet, the blades being arranged so as to form parallel straight rows of blades; (c) bending the metal sheet about a bending axis perpendicular to each row of blades, so as to form a half-tube with annular half-rows of blades which are axially spaced apart, and producing annular grooves by means of rolling; (d) welding annular flanges and axial flanges; (e) application of annular layers of abradable material.

摘要翻译： 本申请涉及一种用于制造轴向涡轮机压缩机的壳体的方法，其具有金属板，该金属板具有环形排的定子叶片，焊接到金属片。 该方法包括以下步骤：（a）提供或生产平面金属片，其具有加工步骤以形成刀片; （b）通过摩擦将定子叶片焊接到金属板的一个平面上，所述叶片被布置成形成平行的直排叶片; （c）围绕垂直于每排叶片的弯曲轴弯曲金属片，以便形成具有轴向间隔开的环形半排叶片的半管，并通过滚动产生环形槽; （d）焊接环形凸缘和轴向凸缘; （e）施加耐磨材料的环形层。

公开(公告)号：US20150300182A1

公开(公告)日：2015-10-22

申请号：US14647679

申请日：2013-11-26

申请人： SNECMA

发明人： Jean-Baptiste Mottin ,  Marc Jacky Vassault

IPC分类号： F01D5/30 ,  B23K20/26 ,  B23K20/12 ,  F01D5/00 ,  F01D5/02

CPC分类号： F01D5/3061 ,  B23K20/1205 ,  B23K20/1295 ,  B23K20/26 ,  B23K2101/001 ,  B23P6/005 ,  F01D5/005 ,  F01D5/02 ,  F05D2220/30 ,  F05D2230/239 ,  F05D2230/60 ,  F05D2230/80 ,  F05D2240/24

摘要： A method of friction welding an airfoil (32) onto a rotor disk of a turbine engine, the disk having at its outer periphery a projecting stub (18) onto which the airfoil is to be welded, the method comprising a step consisting in mounting chocks (24) on leading and trailing edges of the stub, the method being characterized in that, before friction welding, the chocks are secured to the stub by welding, and in that during the friction welding operation, the beads of welding (28) between the chocks and the stub are expelled, at least in part, in seams of material (34) that form around the connection zone between the airfoil and the stub and that are subsequently to be removed or eliminated, e.g. by machining.

摘要翻译： 一种将翼型件（32）摩擦焊接到涡轮发动机的转子盘上的方法，该盘在其外周具有要被焊接翼型的突出短截线（18），该方法包括安装轴承座 （24），所述方法的特征在于，在摩擦焊接之前，通过焊接将所述轴承座固定在所述坯料上，并且在摩擦焊接操作期间，在 至少部分地，轴承座和短截线被排出在材料（34）的接缝之间，所述接缝形成在翼型件和短棒之间的连接区域周围并且随后被移除或消除，例如 通过加工。

公开(公告)号：US09027404B2

公开(公告)日：2015-05-12

申请号：US13473853

申请日：2012-05-17

申请人： Surendra Singh ,  Frederick William Vensel ,  Robert John Hogan ,  Vincent Chung

发明人： Surendra Singh ,  Frederick William Vensel ,  Robert John Hogan ,  Vincent Chung

IPC分类号： G01N29/04 ,  G01N29/44 ,  G01N29/26 ,  G01N29/06

CPC分类号： G01N29/043 ,  F01D5/34 ,  F05D2230/239 ,  F05D2260/80 ,  G01N29/069 ,  G01N29/262 ,  G01N29/265 ,  G01N29/30 ,  G01N29/4436 ,  G01N2291/267 ,  G01N2291/2693

摘要： The disclosed embodiments generally relate to non-destructive evaluation methods. More particularly, the disclosed embodiments relate to ultrasonic non-destructive evaluation methods for the evaluation of friction welded bladed discs (“blisks”). In an embodiment, a method for non-destructive evaluation of a bladed disc structure includes identifying a region of interest on the bladed disc structure; positioning an ultrasonic transducer and receiver in the region of interest; scanning the region of interest using the ultrasonic transducer and receiver to produce a scan image; and comparing the scan image against a reference image to determine the presence of an anomaly in the region of interest.

摘要翻译： 所公开的实施例通常涉及非破坏性评估方法。 更具体地，所公开的实施例涉及用于评估摩擦焊接叶片盘（“叶片”）的超声波非破坏性评估方法。 在一个实施例中，一种用于对盘形盘结构进行非破坏性评估的方法包括识别刀片​​盘结构上的感兴趣区域; 将超声换能器和接收器定位在感兴趣的区域中; 使用超声波换能器和接收器扫描感兴趣区域以产生扫描图像; 以及将扫描图像与参考图像进行比较以确定感兴趣区域中是否存在异常。