公开(公告)号：US09869189B2

公开(公告)日：2018-01-16

申请号：US14647679

申请日：2013-11-26

Applicant: Snecma

Inventor： Jean-Baptiste Mottin ,  Marc Jacky Vassault

IPC: F01D5/30 ,  B23P6/00 ,  B23K20/12 ,  B23K20/26 ,  F01D5/00 ,  F01D5/02 ,  B23K101/00

CPC classification number: 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

Abstract: 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.

公开(公告)号：US20150308984A1

公开(公告)日：2015-10-29

申请号：US14693966

申请日：2015-04-23

Applicant: SNECMA

Inventor： Richard Michael COULETTE ,  Laurent Le Ber ,  Pascal Jean-Christian Claude Ravault ,  Marc Jacky Vassault

IPC: G01N29/265 ,  G01N29/04 ,  G01N29/24

CPC classification number: G01N29/265 ,  G01N29/043 ,  G01N29/223 ,  G01N29/24 ,  G01N29/26 ,  G01N29/262 ,  G01N29/4436 ,  G01N2291/0422 ,  G01N2291/056 ,  G01N2291/106 ,  G01N2291/267 ,  G01N2291/2693 ,  Y10S901/44

Abstract: Method and device for ultrasound testing of welds, particularly for welds of blades on the blisk of a bladed disk.According to the invention, for testing element welds (6) on a body (4), forming a single-piece assembly (2) with these elements, the free end of a poly-articulated robot (12) is fitted with an ultrasound probe (24), fitted with an ultrasonic multi-element array transducer (14); the probe is inserted into the space (10) between two adjacent elements of the assembly; the probe is moved along three-dimensional trajectories along the profile of the element; sectorial electronic scanning is performed in at least two non-parallel testing planes; and ultrasound signals output by the transducer in order to test the welds are processed.

Abstract translation: 用于焊缝超声波测试的方法和装置，特别是对于叶片盘片上的叶片焊缝。 根据本发明，为了在主体（4）上测试元件焊缝（6），用这些元件形成单件式组件（2），多关节机器人（12）的自由端配有超声波探头 （24），配有超声波多元件阵列换能器（14）; 探针插入到组件的两个相邻元件之间的空间（10）中; 沿着元件轮廓的三维轨迹移动探头; 在至少两个非平行测试平面中执行扇区电子扫描; 并且由传感器输出的用于测试焊缝的超声波信号被处理。

公开(公告)号：US09321125B2

公开(公告)日：2016-04-26

申请号：US13935883

申请日：2013-07-05

Applicant: SNECMA

Inventor： Marc Jacky Vassault

IPC: B23K20/12 ,  B23K33/00

CPC classification number: B23K20/12 ,  B23K20/129 ,  B23K33/006 ,  B23K2101/06 ,  Y10T403/477

Abstract: A system includes a unit of a first part, and a proximal portion through an intermediate portion extended by a distal portion including a first extremity surface. A second part with a second portion includes a second surface to be friction welded with the extremity surface. A second portion is bordered laterally by a lateral surface and has a proximal portion, which extends through an intermediate portion extended by a distal portion. The distal portion of the second portion is carried in a malleable state during a friction welding. The intermediate portion of the second portion flares from the distal portion by the second towards and till the proximal portion of the second portion such that the bead of material from the deformation of the distal portion of the second portion during welding rubs against the lateral surface of the intermediate portion of the second portion during welding.

Abstract translation: 系统包括第一部分的单元和通过包括第一末端表面的远端部分延伸的中间部分的近端部分。 具有第二部分的第二部分包括与末端表面摩擦焊接的第二表面。 第二部分由侧面横向地界定并且具有近端部分，该近端部分延伸穿过由远侧部分延伸的中间部分。 第二部分的远端部分在摩擦焊接期间承载在可延展的状态。 第二部分的中间部分从第二部分向第二部分向第二部分的近端部分展开，使得在焊接期间来自第二部分的远端部分的变形的材料珠沿着 在焊接期间第二部分的中间部分。

公开(公告)号：US20150300182A1

公开(公告)日：2015-10-22

申请号：US14647679

申请日：2013-11-26

Applicant: SNECMA

Inventor： Jean-Baptiste Mottin ,  Marc Jacky Vassault

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

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。