An electron beam welding appliance (10), characterised in that it comprises: an electron gun (11) capable of generating an electron beam (FE); a focusing means (12) capable of orienting the electron beam along a first axis (Z); an arm (13) extending parallel to the first axis, the arm comprising: a means (14) for converting a density distribution of the electron beam in a plane perpendicular to the first axis (Z); and a means (15) for bypassing the electron beam along a second axis (X) substantially perpendicular to the first axis.

An electron beam welding appliance (10), characterised in that it comprises: an electron gun (11) capable of generating an electron beam (FE); a focusing means (12) capable of orienting the electron beam along a first axis (Z); an arm (13) extending parallel to the first axis, the arm comprising: a means (14) for converting a density distribution of the electron beam in a plane perpendicular to the first axis (Z); and a means (15) for bypassing the electron beam along a second axis (X) substantially perpendicular to the first axis.

A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

In some embodiments, a method may bond titanium to an intermediate alloy. The method may include layering a portion of an intermediate alloy onto a portion of titanium. The method may include focusing a controlled heat source on a spot of the intermediate alloy to form a weld pool in the intermediate alloy at the spot. The method may include superheating the intermediate alloy in the weld pool above the melting point of the intermediate alloy but below the melting point of titanium such that liquid intermediate alloy contacts the surface of the portion of the titanium heating the portion of the titanium. The method may include diffusing the portions of titanium and intermediate alloy together such that upon the intermediate alloy cooling below the melting point of the intermediate alloy the portions of the intermediate alloy and titanium are bonded forming a weldment.

A method of repairing a rod guide assembly of a fuel control unit of an aircraft engine is provided. The method comprises disconnecting a used spring seat from the rod of the rod guide assembly and welding a replacement spring seat to the rod using an electron beam controlled using a circular beam deflection pattern.

Disclosed herein is a method of forming a multi-layered metallic part. The method comprises stacking at least two metallic layers, each made of a metallic material having a ductility, to form a multi-layered metallic assembly. The method also comprises interposing a diffusion-bond preventing element directly between adjacent ones of the at least two metallic layers of the multi-layered metallic assembly. The method further comprises diffusion bonding the at least two metallic layers to each other at locations other than a location contiguous with the diffusion-bond preventing element to produce a multi-layered metallic part having a non-bonded region between the at least two metallic layers at the location of the diffusion-bond preventing element.

In some embodiments, a method may bond titanium to an intermediate alloy. The method may include layering a portion of an intermediate alloy onto a portion of titanium. The method may include focusing a controlled heat source on a spot of the intermediate alloy to form a weld pool in the intermediate alloy at the spot. The method may include superheating the intermediate alloy in the weld pool above the melting point of the intermediate alloy but below the melting point of titanium such that liquid intermediate alloy contacts the surface of the portion of the titanium heating the portion of the titanium. The method may include diffusing the portions of titanium and intermediate alloy together such that upon the intermediate alloy cooling below the melting point of the intermediate alloy the portions of the intermediate alloy and titanium are bonded forming a weldment.

An outer joint member of a constant velocity universal joint includes a cup section having track grooves formed in an inner periphery thereof, which are engageable with torque transmitting elements, and a shaft section formed at a bottom portion of the cup section. The cup section and the shaft section are formed as separate members, and by bringing a cup member forming the cup section and a shaft member forming the shaft section into abutment against each other at respective joining end surfaces and welding them, a hollow cavity portion is formed. The cup member has, at an axial center, a ventilation hole that communicates with the hollow cavity portion and any one of the joining end surfaces of the cup member and the joining end surface of the shaft member has a welding spatter receiving groove formed on a radially inner side thereof.

An outer joint member of a constant velocity universal joint includes a cup section having track grooves formed in an inner periphery thereof, which are engageable with torque transmitting elements, and a shaft section formed at a bottom portion of the cup section. The cup section and the shaft section are formed as separate members, and by bringing a cup member forming the cup section and a shaft member forming the shaft section into abutment against each other at respective joining end surfaces and welding them, a hollow cavity portion is formed. The cup member has, at an axial center, a ventilation hole that communicates with the hollow cavity portion and any one of the joining end surfaces of the cup member and the joining end surface of the shaft member has a welding spatter receiving groove formed on a radially inner side thereof.

A method for assembling at least two parts includes using transparent welding using an energy input beam which travels a trajectory in a closed loop. The trajectory of the energy input beam and/or at least one parameter of the energy input beam is configured so that the weld bead has mechanical and/or geometrical characteristics that are substantially constant over all its length. A method for assembling a primary structure of an aircraft pylon which uses this assembly method to link the panels of the primary structure to one another, a primary structure of an aircraft pylon thus obtained, as well as an aircraft comprising at least one such primary structure is also described.