公开(公告)号：US09713855B2

公开(公告)日：2017-07-25

申请号：US14404513

申请日：2013-05-30

Applicant: SNECMA

Inventor： Yves Le Meur ,  Jean-Baptiste Mottin

IPC: B23K26/38 ,  H01S3/042 ,  B23K26/14 ,  H01S3/093 ,  H01S3/102 ,  B23K26/0622 ,  B23K26/382 ,  B23K101/00 ,  H01S3/04 ,  H01S3/06 ,  H01S3/16

CPC classification number: B23K26/1435 ,  B23K26/0622 ,  B23K26/382 ,  B23K26/389 ,  B23K2101/001 ,  H01S3/0407 ,  H01S3/061 ,  H01S3/093 ,  H01S3/1028 ,  H01S3/1643

Abstract: A method of drilling a part, or a turbine engine part, by a pulse laser generator including a cavity in which there is mounted a solid bar for generating laser pulses, the method including determining values of a plurality of operating parameters of the laser generator for forming orifices of predetermined diameter in the part, and taking account, among the parameters, of a setpoint value for the temperature of the laser cavity, which value is determined as a function of characteristics of the orifices to be drilled.

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。

公开(公告)号：US11117215B2

公开(公告)日：2021-09-14

申请号：US14399751

申请日：2013-05-07

Applicant: SNECMA

Inventor： Jean-Baptiste Mottin

IPC: B23K26/12 ,  B23P6/00 ,  B23K26/34 ,  B22F5/00 ,  B22F5/04 ,  B23K35/02 ,  B23K26/342 ,  B23K26/144 ,  B23K26/32 ,  B22F10/20 ,  B23K15/00 ,  B22F7/06 ,  B23K103/08 ,  B23K103/14 ,  B23K103/18 ,  B23K103/00 ,  B23K101/00 ,  B23K103/10

Abstract: A method for hard-surfacing metal parts for an aircraft turbofan, the method involving the use of a nozzle outputting a laser beam or an electron beam, which is to heat a sprayed powder for hard-surfacing the metal part, the method including positioning the metal part to be hard-surfaced in an enclosure, the top portion of which has an opening; positioning a mobile cover covering the opening of the top portion, the mobile cover having an opening; positioning the nozzle at the opening of the mobile cover; feeding an inert gas into the enclosure; spraying metal powders and emitting the laser or electron beam for hard-surfacing the metal part; moving the nozzle relative to the enclosure along a path for hard-surfacing the metal part, the movement of the nozzle causing the movement of the mobile cover on the top surface of the enclosure.

公开(公告)号：US20150114938A1

公开(公告)日：2015-04-30

申请号：US14399751

申请日：2013-05-07

Applicant: SNECMA

Inventor： Jean-Baptiste Mottin

IPC: B23K26/34 ,  B23K26/12 ,  B23K26/14 ,  B23P6/00 ,  B23K15/00

CPC classification number: B23K26/12 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F2007/068 ,  B23K15/0086 ,  B23K26/144 ,  B23K26/32 ,  B23K26/34 ,  B23K26/342 ,  B23K35/0244 ,  B23K2101/001 ,  B23K2103/08 ,  B23K2103/10 ,  B23K2103/14 ,  B23K2103/26 ,  B23K2103/50 ,  B23P6/007 ,  Y02P10/295

Abstract: A method for hard-surfacing metal parts for an aircraft turbofan, the method involving the use of a nozzle outputting a laser beam or an electron beam, which is to heat a sprayed powder for hard-surfacing the metal part, the method including positioning the metal part to be hard-surfaced in an enclosure, the top portion of which has an opening; positioning a mobile cover covering the opening of the top portion, the mobile cover having an opening; positioning the nozzle at the opening of the mobile cover; feeding an inert gas into the enclosure; spraying metal powders and emitting the laser or electron beam for hard-surfacing the metal part; moving the nozzle relative to the enclosure along a path for hard-surfacing the metal part, the movement of the nozzle causing the movement of the mobile cover on the top surface of the enclosure.

Abstract translation: 一种用于飞机涡扇风扇的金属部件的硬表面的方法，该方法包括使用输出激光束或电子束的喷嘴，该方法是加热用于硬表面金属部件的喷涂粉末，该方法包括将 金属部分要在外壳中硬表面，其顶部具有开口; 定位覆盖顶部开口的活动盖，该移动盖具有开口; 将喷嘴定位在移动盖的开口处; 将惰性气体送入外壳; 喷射金属粉末并发射激光或电子束，以硬化表面金属部分; 沿着用于硬表面金属部件的路径相对于外壳移动喷嘴，喷嘴的运动导致移动盖在壳体的顶表面上的移动。

公开(公告)号：US20140217068A1

公开(公告)日：2014-08-07

申请号：US14347565

申请日：2012-09-27

Applicant: SNECMA ,  UNIVERSITÉ DE NANTES ,  UNIVERSITÉ PARIS SUD (UPS) ,  CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, (C.N.R.S.)

Inventor： Jean-Baptiste Mottin ,  Jean-François Castagne ,  Thierry Baudin ,  Alexandre Yann Michel Benoit ,  Pascal Paillard

IPC: B23P6/00 ,  B23K9/173 ,  B23K9/04

CPC classification number: B23K9/173 ,  B23K9/04 ,  B23K9/046 ,  B23K9/09 ,  B23K26/32 ,  B23K26/342 ,  B23K35/0261 ,  B23K35/286 ,  B23K2101/001 ,  B23K2103/08 ,  B23K2103/10 ,  B23K2103/18 ,  B23K2103/20 ,  B23P6/007 ,  F01D21/045 ,  F01D25/243 ,  F05D2230/235 ,  F05D2230/30 ,  F05D2230/80

Abstract: A method for hard surface deposition on aluminium metal parts of a turbine engine using MIG welding equipment which includes a pulsed current generator and pulsed filler metal wire feed, wherein the deposition is achieved using a filler metal wire whose composition is of the same nature as the composition of the aluminium alloy of the part to undergo hard surface deposition, with the pulsed metal wire feed and speed of deposition on the metal part of the turbine engine being adapted to carry out deposition without hot fissuring.

Abstract translation: 一种用于使用包括脉冲电流发生器和脉冲填充金属线进给的MIG焊接设备在涡轮发动机的铝金属部件上进行硬表面沉积的方法，其中使用填充金属线实现沉积，所述填充金属线的组成与 通过在涡轮发动机的金属部分上的脉冲金属丝进料和沉积速度适于在没有热裂纹的情况下进行沉积，部分的铝合金的组成经历硬表面沉积。

公开(公告)号：US11148204B2

公开(公告)日：2021-10-19

申请号：US14647519

申请日：2013-11-27

Applicant: SNECMA ,  MBDA FRANCE

Inventor： Christophe Colin ,  Jean-Baptiste Mottin ,  Laëtitia Kirschner ,  Gérard Saussereau

IPC: B22F10/20 ,  C04B35/64 ,  B28B1/00 ,  C22C19/05 ,  B33Y10/00 ,  B22F1/00 ,  B29C64/153 ,  B22F3/105 ,  B29L31/00 ,  B33Y70/00 ,  B22F10/30

Abstract: A method for fabricating a part by selective melting or sintering of powder beds by high energy beam, the method including a) providing a material in the form of powder particles; b) depositing a first powder layer on a support; c) scanning a region of the first layer with the beam to heat the powder locally to a temperature higher than the powder sintering temperature, such that the powder particles as melted or sintered form a first single-piece element; d) depositing a second powder layer on the first powder layer; e) scanning a region of the second layer with the beam to heat the powder to a temperature higher than the powder sintering temperature, so that the particles of powder as sintered or melted form a second single-piece element; and f) repeating d) and e) for each new powder layer laid over a preceding layer until the part is formed.

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：US09731373B2

公开(公告)日：2017-08-15

申请号：US14347565

申请日：2012-09-27

Applicant: SNECMA ,  CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (C.N.R.S.) ,  UNIVERSITÉ PARIS SUD (UPS) ,  UNIVERSITÉ DE NANTES

Inventor： Jean-Baptiste Mottin ,  Jean-François Castagne ,  Thierry Baudin ,  Alexandre Yann Michel Benoit ,  Pascal Paillard

IPC: B23K9/04 ,  B23K9/09 ,  B23K9/173 ,  B23P6/00 ,  F01D25/24 ,  F01D21/04 ,  B23K26/32 ,  B23K26/342 ,  B23K35/28 ,  B23K35/02 ,  B23K101/00 ,  B23K103/20 ,  B23K103/08 ,  B23K103/10 ,  B23K103/18

CPC classification number: B23K9/173 ,  B23K9/04 ,  B23K9/046 ,  B23K9/09 ,  B23K26/32 ,  B23K26/342 ,  B23K35/0261 ,  B23K35/286 ,  B23K2101/001 ,  B23K2103/08 ,  B23K2103/10 ,  B23K2103/18 ,  B23K2103/20 ,  B23P6/007 ,  F01D21/045 ,  F01D25/243 ,  F05D2230/235 ,  F05D2230/30 ,  F05D2230/80

Abstract: A method for hard surface deposition on aluminum metal parts of a turbine engine using MIG welding equipment which includes a pulsed current generator and pulsed filler metal wire feed, wherein the deposition is achieved using a filler metal wire whose composition is of the same nature as the composition of the aluminum alloy of the part to undergo hard surface deposition, with the pulsed metal wire feed and speed of deposition on the metal part of the turbine engine being adapted to carry out deposition without hot fissuring.

公开(公告)号：US09694444B2

公开(公告)日：2017-07-04

申请号：US14905623

申请日：2014-07-15

Applicant: SNECMA

Inventor： Jean-Baptiste Mottin

IPC: B23K26/34 ,  B23K26/144 ,  B05B15/00 ,  B23K26/12 ,  B23K26/14 ,  B23K26/342 ,  B23K101/00 ,  B23K101/34

CPC classification number: B23K26/34 ,  B05B15/16 ,  B23K26/127 ,  B23K26/128 ,  B23K26/144 ,  B23K26/1462 ,  B23K26/342 ,  B23K2101/001 ,  B23K2101/35

Abstract: A protection cover suitable for being placed between a spray nozzle and a metal part during a process of resurfacing the metal part, the protection cover including a side wall extending along a reference axis, the side wall including an inner surface and an outer surface, the side wall having a lower end and an upper end, the side wall being perforated by at least one lateral gas inlet port, the lower end of the side wall being perforated by a notch into which a portion of the metal part can be inserted, the upper end of the side wall being provided with an opening into which a portion of the spray nozzle can be inserted. The inner surface of the side wall includes at least one frustoconical portion.

公开(公告)号：US20150165561A1

公开(公告)日：2015-06-18

申请号：US14404513

申请日：2013-05-30

Applicant: SNECMA

Inventor： Yves Le Meur ,  Jean-Baptiste Mottin

IPC: B23K26/38 ,  B23K26/06 ,  B23K26/14

CPC classification number: B23K26/1435 ,  B23K26/0622 ,  B23K26/382 ,  B23K26/389 ,  B23K2101/001 ,  H01S3/0407 ,  H01S3/061 ,  H01S3/093 ,  H01S3/1028 ,  H01S3/1643

Abstract: A method of drilling a part, or a turbine engine part, by a pulse laser generator including a cavity in which there is mounted a solid bar for generating laser pulses, the method including determining values of a plurality of operating parameters of the laser generator for forming orifices of predetermined diameter in the part, and taking account, among the parameters, of a setpoint value for the temperature of the laser cavity, which value is determined as a function of characteristics of the orifices to be drilled.

Abstract translation: 一种通过包括空腔的脉冲激光发生器来钻出部件或涡轮发动机部件的方法，其中安装有用于产生激光脉冲的实心棒，该方法包括确定激光发生器的多个操作参数的值， 在部件中形成预定直径的孔，并且在参数之中考虑激光腔的温度的设定值，该值被确定为要钻孔的特征的函数。