An object is to provide a variable-geometry exhaust turbocharger including a variable nozzle mechanism in which nozzle supports may not deform under a high-temperature condition. A variable-geometry exhaust turbocharger (1) includes: a nozzle mount (2); a nozzle support (6) having a first end coupled to a first face (2a) of the nozzle mount; a nozzle plate (4) coupled to the second end of the nozzle support and supported to be separated from the first face (2aa) of the nozzle mount, the nozzle plate having a first face (4a) coupled to the nozzle support and a second face (4b) which is opposite to the first face and which faces an exhaust gas channel (20) through which exhaust gas flows: a plurality of nozzle vanes (8) rotatably supported between the nozzle mount and the nozzle plate; and a variable nozzle mechanism (10) configured to change vane angles of the nozzle vanes to control a flow of the exhaust gas flowing between the nozzle mount and the nozzle plate. The nozzle plate is formed of a material having a smaller linear expansion coefficient than that of a material forming the nozzle mount.

A method for manufacturing a turbine engine blade (25) comprising a pressure side and a suction side separated from one another by an inner space for the circulation of cooling air, the blade (25) comprising a tip (S) with a closing wall (29) joining the pressure side and suction side walls in the region of this tip (S) in order to define a well shape, the closing wall including through-holes. The closing wall (29) obtained by moulding has a considerable nominal thickness with pits (36, 37) locally reducing this thickness at each through-hole in order to facilitate the removal by chemical etching of alumina rods defining the holes. Since the closing wall (29) thus has a large nominal thickness, it can then be machined in order to form raised patterns or complex shapes inside the well.

A method and apparatus for vibro-treating an object. The method includes the steps of controlling a relative displacement between a vibro-treating media and a surface area of the object to provide a vibro-treating effect; and, controlling movement of the object relative to a surface of the vibro-treating media whilst controlling relative displacement between the vibro-treating media and the surface area of the object, according to one or more pre-determined conditions, to provide a substantially even vibro-treating condition over the surface area of the object.

The present invention relates to a relief valve (1) for a turbocharger, in which the crank arm (3) is made of a first material and the shaft (4) is made of a second material different from the first material used for manufacturing the crank arm (3), each of the materials containing a composition that provides the necessary properties according to the application of each component of the relief valve (1). The present invention also relates to a process for manufacturing the relief valve (1), which allows the crank arm (3) and the shaft (4) to be manufactured separately, using different materials for the manufacture of each component.

A die cast system in which an external shell and an internal core usable to form a component of a gas turbine engine are formed together is disclosed. In at least one embodiment, the external shell and internal core may be formed from at the same time via a selective laser melting process, thus eliminating the need for using the conventional lost-wax casting system. In at least one embodiment, the external shell and internal core may be formed a ceramic material that may support receiving molten metal to form a turbine component. Once formed, the external shell and internal core may be removed to reveal the turbine component.

A method for producing a rotary disk/blisk for a high-pressure compressor or a high-speed turbine and to a corresponding geared turbofan engine. The method involves providing a Ni base alloy comprising, in % by weight, 15.5-16.5 Cr, 14.0-15.5 Co, 4.75-5.25 Ti, 2.75-3.25 Mo. 2.25-2.75 Al, 1.00-1.50 W, as well as optionally 0.0250-0.0500 Zr, 0.0100-0.0200 B, 0.0100-0.0200 C, remainder Ni. The base alloy is shaped by forging to obtain a preform of the disk/blisk, the final contour thereof being produced by electrical discharge machining or electrochemical machining.

A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.

Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.

A method of joining a first work piece and a second workpiece. The first and second workpieces may be rotor wheels of a rotor for a turbomachine. At least one of the workpieces includes an oxide dispersion strengthened alloy material and the first and second work pieces may be joined by welding a cladding on at least one of the workpieces to the other of the workpieces, without welding a substrate of the at least one workpiece which includes an oxide dispersion strengthened alloy material.

An edge guard apparatus for an airfoil includes: a body having a nose section with spaced-apart first and second sidewalls extending therefrom, the body defining a cavity between the first and second sidewalls; and internal bracing disposed in the cavity, the internal bracing including at least one cross-member extending between the first and second sidewalls.