A foundry mix includes a major amount of a foundry aggregate and an effective binding amount of a binder system. The binder system cures in the presence of sulfur dioxide and a free radical initiator. The binder system may include (1) 10 to 70 parts by weight of an epoxy novolac resin; (2) 0.5 to 10 parts by weight of resorcinol; (3) 20 to 70 parts by weight of a monomeric or polymeric acrylate; and (4) an effective amount of a free radical initiator. Notably, (1), (2), (3) and (4) are separate components or mixed with another of said components, provided (4) is not mixed with (3), where said parts by weight are based upon 100 parts of the binder system.

A foundry mix includes a major amount of a foundry aggregate and an effective binding amount of a binder system. The binder system cures in the presence of sulfur dioxide and a free radical initiator. The binder system may include (1) 10 to 70 parts by weight of an epoxy novolac resin; (2) 0.5 to 10 parts by weight of resorcinol; (3) 20 to 70 parts by weight of a monomeric or polymeric acrylate; and (4) an effective amount of a free radical initiator. Notably, (1), (2), (3) and (4) are separate components or mixed with another of said components, provided (4) is not mixed with (3), where said parts by weight are based upon 100 parts of the binder system.

A method of making a composite core includes forming first and second cores of refractory metal and ceramic material. Each of the first and second cores is formed with two layers of a material. The layers are bonded together to form a laminate master pattern, and a flexible mold is formed around the pattern. The pattern is removed from the flexible mold, and slurry material, either pulverulent refractory metal material or ceramic material, is poured into the flexible mold. The slurry material is sintered to form each core. The first core is used as an insert while making the second core to create a final composite core.

A method of making a refractory metal core includes forming two layers of the core out of a material. The layers are bonded together to form a laminate master pattern, and a flexible mold is formed around the pattern. The pattern is removed from the flexible mold, and pulverulent refractory metal material is poured into the flexible mold. The pulverulent refractory metal material is sintered to form the refractory metal core.

Manufacturing assemblies and molds are provided herein. The manufacturing assembly includes a tool base, a plurality of tool elements extending from the tool base, the plurality of tool elements defining a shape of a formed part, with a cell formed between adjacent tool elements, and a tapered tool extension extending between the tool base and at least one tool element.

A method is for producing a profile segment of a segmented casting-vulcanizing mold for vehicle tires, the molding area of which molds a segment of the tread profile of a tire to be vulcanized, including the steps: creating a rigid model segment having a casing-like tread surface; milling the profile positive of the tread into the casing-like tread surface of the model segment to obtain the master model; creating a flexible impression from the master model; creating a rigid plaster cast from the impression to form a casting core segment; casting all of the annular, placed-together casting core segments with an aluminium-magnesium alloy to obtain a vulcanizing mold, subsequently divided into profile segments. A plasma coating is applied to the tread of the model segment, into which the profile positive of the tread is subsequently milled to obtain the master model. Plasma coating gives the master model a defined roughness.

An end or intermediate casing for a combustion turbine engines includes prefabricated vanes of a first metal. Ends of the prefabricated vanes are then embedded within cast-in place inner and outer, annular-shaped ring castings, formed from a second metal having a lower melting point than the first metal. The respective ends of the prefabricated vanes include first and second shanks, with respective first and second surface features that are oriented transverse to the central axis of the vane are encapsulated in the molten second metal during the inner and outer ring casting. Once the castings harden, the first and second surface features, such as for example circumferential fillets projecting outwardly from the airfoil portion of the vane, inhibit separation of the vanes from the respective inner and outer rings.

An end or intermediate casing for a combustion turbine engines includes prefabricated vanes of a first metal. Ends of the prefabricated vanes are then embedded within cast-in place inner and outer, annular-shaped ring castings, formed from a second metal having a lower melting point than the first metal. The respective ends of the prefabricated vanes include first and second shanks, with respective first and second surface features that are oriented transverse to the central axis of the vane are encapsulated in the molten second metal during the inner and outer ring casting. Once the castings harden, the first and second surface features, such as for example circumferential fillets projecting outwardly from the airfoil portion of the vane, inhibit separation of the vanes from the respective inner and outer rings.

The present invention relates to a method of manufacturing a metal mold for replicating a component having a predetermined three-dimensional shape, the manufacturing method comprising: (a) fabricating a glass-based mold by using a moldable nanocomposite comprising an organic binder and glass particles dispersed therein, the glass-based mold having the predetermined three-dimensional shape; and (b) replicating the glass-based mold obtained in step (a) by melting a metal inside the glass-based mold or by melting a metal outside the glass-based mold and pouring it onto or into the glass-based mold, followed by cooling, or by pressing the glass-based mold into a malleable metal substrate, thereby obtaining the metal mold for replicating the component, the metal mold having the predetermined three-dimensional shape inverted. Further, the present invention relates to a method of replicating a component having a predetermined three-dimensional shape, wherein the metal mold obtained by the manufacturing method is used for replicating the component, wherein the glass particles of the moldable nanocomposite comprise a first type of glass particles having a diameter in the range from 5 nm to 500 nm.

A release agent is disclosed for use with an organic binder system used in metal casting. The binder system has a Part I component including an epoxy resin and a free radical initiator and a Part II component having an epoxy resin and an acrylate, where the Part I and Part II components are kept separate until the time of use. The release agent will typically have a molecular weight in the range of 150 to 160, with eight to ten carbon atoms. Two examples of the epoxide are pinene oxide and decene-1 oxide, each of which is effective as an internal release agent when present in the binder for a cold box process in the range of about 0.15% to about 1% of the total weight of the Part I and Part II components.