A turbocharger wheel (4) and shaft (1) assembly exhibits a frustoconical geometry of welding zone contact surfaces extending to the outer circumference of the shaft (1). This frustoconical geometry not only allows continuous centering of the parts (1, 4) during joining, it also eliminates the problem of stress propagation along a plane. The location of the electron beam is shifted so that only the radially outer segment of the frustoconical contact surface is joined by welding, leaving a radially inner unmelted and unfused zone for maintaining firm contact of the oblique surfaces.

A method of manufacturing an outer joint member of a constant velocity universal joint includes forming cup and shaft members of medium carbon steel, preparing, as the cup member, a cup member having cylindrical and bottom portions integrally formed by forging, and a joining end surface formed on an outer surface of the bottom portion, and preparing, as the shaft member, a shaft member having a joining end surface to be joined to the bottom portion of the cup member. The method also includes bringing the joining end surfaces of the cup and shaft members into abutment against each other, and welding the cup and shaft members from an outer side of the cup member to an abutment portion between the cup and shaft members in a radial direction of the cup members.

A method of manufacturing an airfoil includes creating a plurality of cavities separated by a plurality of internal ribs in an airfoil forging. At least one hole is drilled in at least one of the plurality of internal ribs with a waterjet drilling tool. At least one hole extends perpendicularly to a wall of the rib.

An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

An object is to provide a structure and a method of joining a nozzle vane and a lever, and a variable geometry turbocharger, capable of reducing breakage of a welded part between a shaft portion of the nozzle vane and the lever during usage of the same by reducing generation of a hot crack in weld metal at the welded part. A joint structure includes: a nozzle vane 2 disposed in an exhaust passage for guiding exhaust gas to a turbine wheel 34 of a variable geometry turbocharger 500, and including a shaft portion 2a; and a lever 1 including a fitting surface 42a fitted with a peripheral surface 72 on one end side of the shaft portion, for transmitting torque to the shaft portion to adjust a vane angle of the nozzle vane. Weld metal 50 at a welded part 40 between the lever and the nozzle vane is formed so that a center position 64 of the weld metal is disposed inside a position 17 of the fitting surface with respect to a radial direction of the shaft portion.

Disclosed is an improved method of manufacturing cooled accelerator grid with full penetration weld configuration. In a preferred form, the method includes the steps of: machining a plurality of stubs, a first and a second end of a plurality of inconel pipes; welding the stubs with the first end of the inconel pipes forming a water connector assembly; machining of a base plate; welding the base plate with the water connector assembly; machining the base plate welded with the water connector assembly, wherein machining further comprises milling of plurality of cooling channels across angled plane of the base plate welded with the water connector assembly; closing of plurality of cooling channels located on the base plate welded with the water connector assembly; and welding each of plurality of external hydraulic circuits with the second end of each of the plurality of inconel pipes.

A metallic positive expulsion fuel tank with stress free weld seams may include a first hemispherical shell with a first edge; and a hemispherical rolling metal diaphragm with a first edge attached to the first hemispherical shell along matching first edges. A second hemispherical shell with a first edge may be attached to the first edge of the first hemispherical shell by a first weld seam thereby forming two interior chambers separated by the hemispherical rolling metal diaphragm. A pressurized gas inlet may be attached to the first hemispherical dome; and a fuel outlet fixture may be attached to the second hemispherical dome. The first weld seam may have been stress relieved by a localized post-weld heat treatment confined to an immediate vicinity of the first weld seam.

Disclosed are a special tooling and method for electron beam welding of a cavity body and a beam tube of a superconducting niobium cavity. The special tooling includes a first clamping device for fixing a flange and a second clamping device for fixing a semi-cavity body, wherein the first clamping device and the second clamping device are fixedly connected. A pressing ring of the first clamping device is disposed around a beam tube of a superconducting niobium cavity and cooperates with a base plate to clamp and fix the flange. The second clamping device includes clamping arms evenly distributed along a circumference of the semi-cavity body, and each clamping arm includes a second pressing plate axially disposed along the beam tube and a pressing block that is disposed on an end portion of the second pressing plate and fixes an edge of the semi-cavity body.

A method for fabricating a thrust chamber liner for a rocket engine commences with a ring made from a first material on a build plate. A base layer of a second material in powder form is deposited on the exposed axial end of the ring. A laser beam is directed towards the base layer and the ring such that energy associated with the laser beam melts the base layer and a portion of the ring adjacent to the base layer. A melted portion of the base layer intermixes with a melted portion of the ring. Following this step, additional layers of the second material are deposited on the base layer. The first axial end of the ring is then exposed and additional layers of the first material are deposited on the first axial end of the ring.

The fatigue strength of a lap-welded joint, wherein an overlapping portion of a first steel material and an overlapping portion of a second steel material overlap with each other, and an edge portion of the first steel material is welded to a front face of the second steel material with a weld zone extending along the edge portion, is improved. First, when a direction perpendicular to an extending direction X of the weld zone and parallel to a front face of the second steel material is defined as a reference direction Y, the lap-welded joint is restrained from moving in the reference direction Y, and the first steel material and the second steel material are restrained from moving in their sheet-thickness directions. In this state, a portion of the second steel material is heated such that a melted portion is formed in the portion of the second steel material.