A thermos cup vacuumizing device and method are provided. The thermos cup vacuumizing device includes a pre-vacuumizing chamber, a heating chamber, a welding chamber, and a cooling chamber. A continuous conveying device is provided at a bottom of each of the chambers. The thermos cup vacuumizing device further includes a controllable and movable laser welding device and multiple transparent windows. A laser beam of the laser welding device passes through the transparent windows to melt a welding ball at provided at a hole in the center of the bottom of the thermos cup. A vertically movable inlet valve is provided at an inlet of the pre-vacuumizing chamber, and a vertically movable outlet valve is provided at an outlet of the cooling chamber. The present disclosure realizes the continuous vacuumizing operation on the thermos cups, improves the product qualification rate and processing efficiency, and realizes automatic mass production.

A method for shaping a shape memory workpiece includes: providing a shape memory workpiece having a first diameter and a predetermined shaping temperature; arranging the shape memory workpiece on a shaping tool; heating the shape memory workpiece to the shaping temperature; first expansion of the shape memory workpiece to a second diameter that is larger than the first diameter; first changing of the temperature of the shape memory workpiece to an intermediate temperature below or above the shaping temperature; bringing the shape memory workpiece to the shaping temperature again; second expansion of the shape memory workpiece to a third diameter that is larger than the second diameter; ejecting the shape memory workpiece from the shaping tool; and final cooling of the shape memory workpiece to a cooling temperature below the intermediate temperature.

A shaping tool is also provided.

In a method for producing a rail-shaped hybrid component, in particular for an aircraft or spacecraft, a second rail component made of a titanium material is positioned on a first bar of a first profile rail that is made of a carbon-fiber reinforced plastic material and moved in an advancing direction, in a fixed position relative to the first profile rail, such that a bar portion of the first bar is arranged between a first connecting portion of the second rail component and a second connecting portion of the second rail component, and the second rail component is cohesively connected to the first profile rail. Furthermore, the hybrid component has a first profile rail made of a carbon-fiber reinforced plastic material and a second rail component made of a titanium material.

Provided is a joining method that can prevent a plastic flowing material from flowing out from a butt section and that can reduce the thickness and weight of metal members. The joining method is for joining a first metal member and a second metal member by using a rotary tool comprising a stirring pin, and is characterized in that: the stirring pin comprises a flat surface perpendicular to the rotation axis of the rotary tool and comprises a protruding section protruding from the flat face; and in a friction stirring step, the flat surface is brought into contact with the first metal member and the second metal member, and a front end face of the protruding section is inserted deeper than an upper overlapping section to join an upper front butt section and the upper overlapping section.

A method for brazing a metal part onto a surface of a zirconia component. The method involves the steps of altering the surface state of the component to permit the attachment of a first metallization layer, cleaning the component to eliminate the impurities from its surface, depositing a first metallization layer, having mainly titanium, on the surface of the component, depositing a second metallization layer, having mainly niobium, on the first metallization layer, applying the part against the second metallization layer, depositing a gold brazing metal on the part and the second metallization layer, cooling the brazed area in a temperature-controlled manner, and stress-relieving heat treatment being performed under load on the metal part before brazing.

Within examples, a method of manufacturing a double-walled titanium conduit is described. Example methods include stitch welding multiple concentric sheets to form a stitch layer, providing the stitch layer between an inner wall and an outer wall of the double-walled titanium conduit, circumferentially seam welding the inner wall and the outer wall to the stitch layer to create a welded assembly, die forming the welded assembly at temperature and pressure to form inner structures between the multiple concentric sheets according to stitch welding lines and to enable a diffusion bond process among the inner wall, the stitch layer, and the outer wall, and removing the double-walled titanium conduit from the die.

Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at the respective platform regions by a friction welding method at a common joint region of the platform regions, the blade airfoil and the blade root being made of materials which are different from each other. Also disclosed is a blade which is and/or can be obtained by such a method.

A system may include a current source; a first metal or alloy component with a first major surface electrically coupled to the current source; a second metal or alloy component with a second major surface electrically coupled in series to the first component and the current source via an external electrical conductor, where the first and second major surfaces are positioned adjacent to each other to define a joint region; a metal or alloy powder disposed in at least a portion of the joint region; and a controller. The controller may be configured to cause the current source to output an alternating current that conducts through the first component and the second component to induce magnetic eddy currents, magnetic hysteresis, or both within at least a portion of the metal or alloy powder disposed in at least the first portion of the joint region.

A multi component braze filler alloy is described having a melting temperature less than about 1235 deg. C. and greater than about 1150 deg. C. This alloy can be processed by hot isostatic pressing (HIP) at a temperature above about 1065 deg. C. and is particularly suited for the repair of gas turbine blades and vanes, especially those made from Alloy 247. The relatively low Ti content in the present braze alloy tends to form less MC carbides at the joint interface, particularly in comparison with other braze alloys high in Zr and/or Hf. Processes for employing this braze filler alloy in processing of nickel-base superalloys, especially Alloy 247, are presented.

A joining method including an overlapping step of overlapping a front surface of a first metal member and a back surface of second metal member such that the front surface is opposed to the back surface; and a welding step of performing a laser welding and a MIG welding by using a hybrid welding machine including a preceding laser welding unit and a following MIG welding unit, in which the laser welding is performed by emitting a laser beam onto a front surface of the second metal member, the MIG welding is performed on an inner corner portion formed by the front surface of the first metal member and an end surface of the second metal member, and a target position for the laser beam from the laser welding unit is located against the second metal member relative to a target position for a MIG arc by the MIG welding unit.