Disclosed is a method for producing a blade for a turbomachine, which method comprises: providing a blade root, having a first platform region, from a first material; providing on the first platform region at least one capsule that is filled with a metallic and/or ceramic powder that comprises at least one second material which is different from the first material, for producing a blade airfoil having a second platform region; producing and shaping a blade airfoil from the capsule that is filled with the powder by at least one thermal input method, thereby connecting the blade root to the blade airfoil in respective platform regions.

Also disclosed is a blade which is obtainable and/or obtained by this method.

A ring molded article manufacturing method capable of reliably and efficiently producing a ring molded article in which dead metal regions are reduced, and a ring material used for producing the ring molded article, are provided. The present invention relates to the method for manufacturing a ring molded article having two convex portions which respectively protrude on both sides of the ring molded article in a direction of a center axis thereof and extend in a direction of a circumference of the ring molded article. In the manufacturing method, the ring material is placed inside two molds on which concave portions respectively corresponding to the convex portions are formed, in a condition in which the ring material is supported by a region on an outer peripheral side from an outer peripheral side corner in the concave portion of one of the two molds and a region on an inner peripheral side from an inner peripheral side corner in the concave portion of another of the two molds, the ring material is then forged so as to be pressed by the two molds in a direction of a center axis of the ring material, and the ring molded article is thus produced. In addition, the present invention relates to the ring material used for producing the ring molded article.

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 field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.

Turbomachine member ring supports extending over sectors of a circle can be constructed from at least one thick flat metal sheet that is curved and welded to form a cylindrical shroud and then formed by pressing into a conical shroud, the outer face of which is machined in order to shape the profile of a mounting rail therein, and the shroud is sectioned in order to divide it into the sectors. The supports have better cohesion and the manufacture thereof is simple and reliable compared with traditional manufacture using bossing of thin metal sheets for joining together the main portions of the supports. The application also relates to a use with stator rings of a turbomachine member that are provided with an abradable lining.

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 turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from a coupling head towards the coupling root and formed in one piece with the coupling head; and a main plate-like body which is shaped and positioned between the two connecting fins to form an extension of the fins, and is butt-welded to the same connecting fins to form one piece with the fins.

A method for the manufacture of a blisk drum is described. Disc forging for inertia welding together are provided with sacrificial material whose shape and position is selectively provided such that, on completion of the inertia welding process, integral blades can be fashioned from the sacrificial material. Other components such as buckets and balancing lands may also be provided from the sacrificial material.

Various implementations include a ring material used for producing a ring molded article. The ring molded article has two convex portions which respectively protrude on opposite sides of the ring molded article in a direction of a center axis thereof and extend in a direction of a circumference of the ring molded article. A straight line passing through centers of gravity of first and second side regions is inclined by an angle relative to the center axis of the ring material, the first and second side regions are obtained by virtually dividing a one half section of the ring material based on a middle of a maximum height of the ring material in the direction of the center axis of the ring material, and a range of the angle is 7 degrees to 40 degrees.

A mounting plate for forming a gas turbine engine component according to an example of the present disclosure includes, among other things, a plate body defining an abutment dimensioned to mate with a forming die. The plate body defines at least one internal cooling circuit. The at least one internal cooling circuit includes a passageway having an intermediate portion interconnecting inlet and outlet portions. The intermediate portion is dimensioned to follow a perimeter of the abutment. The intermediate portion includes a plurality of fins extending partially from a first sidewall towards a second sidewall opposed to the first sidewall. A method of forming a gas turbine engine component is also disclosed.