Abstract:
The invention relates to a method for manufacturing a laminated or forged material, the thickness of which is 14 to 100 mm. The materials according to the invention are particularly suitable for manufacturing airplane underwing elements.
Abstract:
An exemplary process includes determining a desired pore size, selecting an initial pore size greater than the target pore size, manufacturing a porous structure with the initial pore size, forging the porous structure to form a forged part having the desired pore size, and forming an orthopedic device from the forged part.
Abstract:
A method to form a magnesium article includes: heating materials including magnesium, aluminum, manganese and tin in a furnace to create an alloy having a composition of; the magnesium in an amount greater than or equal to 90% by weight of the materials; the aluminum ranging between approximately 2.0% up to approximately 4.0% by weight of the materials; the manganese ranging between approximately 0.43% up to approximately 0.6% by weight of the materials; and the tin ranging between approximately 1% up to approximately 3% by weight of the materials; chill casting the alloy to create a cast billet; and heating the cast billet at a temperature ranging from approximately 380° C. up to approximately 420° C. and maintaining the temperature for a time period between approximately 4 hours to 10 hours to homogenize element distribution.
Abstract:
Provided are discs and bores of a gas turbine engine having one or more graphene layers and methods of preparing the same. The one or more graphene layers are disposed adjacent to the disc rim and/or bore to improve heat transfer and reduce oxidation of the discs. Methods of preparing the graphene layers and systems for using the same are provided.
Abstract:
A forging method is provided. The forging comprises determining plans of second and third processes for each of a plurality of ingots, categorizing the plurality of ingots into first and second ingot sets, based on the plans of the second and third processes, evaluating the first and second ingot sets using a scoring function, determining an ingot set to be provided to a first heating furnace, based on the evaluating of the first and second ingot sets, and performing a first process, different from the second and third processes, on the ingot set provided to the first heating furnace.
Abstract:
Systems and methods in accordance with embodiments of the invention implement bulk metallic glass-based macroscale compliant mechanisms. In one embodiment, a bulk metallic glass-based macroscale compliant mechanism includes: a flexible member that is strained during the normal operation of the compliant mechanism; where the flexible member has a thickness of 0.5 mm; where the flexible member comprises a bulk metallic glass-based material; and where the bulk metallic glass-based material can survive a fatigue test that includes 1000 cycles under a bending loading mode at an applied stress to ultimate strength ratio of 0.25.
Abstract:
A sprocket wheel, which is a machine component configured to slide relative to a bushing while being in contact with the bushing in an outer peripheral surface, includes a base made of a first metal, and an overlay that covers the base so as to constitute the outer peripheral surface. The surface of the overlay constituting the outer peripheral surface has been smoothed. Such a smoothed surface of the overlay makes the sprocket wheel less damaging to the bushing.
Abstract:
A method of decorating an element. This method includes the following steps: taking the element (1, 11, 21, 31), the element including anchoring for improving the securing of the decoration (5) to the element; making a mask (4) of the desired thickness of the decorations (5), and having at least one opening (4′); placing the at least one opening in the mask (4) against the place to be decorated so as to form at least one mould (4′, 6, 6′, 6″,100); filling the at least one mould with an at least partially amorphous material via hot forming; and removing the mask (4).
Abstract:
The invention relates to a method for manufacturing a laminated or forged material, the thickness of which is 14 to 100 mm. The materials according to the invention are particularly suitable for manufacturing airplane underwing elements.
Abstract:
The present invention relates to a method of making a timepiece plate. This method is characterized in that it includes the following steps: a) taking (A1, A2) the material forming the plate including at least one metallic element; b) forming (B1, B2) the plate; c) cooling (C) everything so as to obtain the timepiece plate in an at least partially amorphous state; and d) retrieving (D) the plate.