Integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible provide a pathway to restrict cooling flow between turbine blades to the flowpath.

The present disclosure relates to a method of forming a cast component and a method of forming a casting mold. The method is performed by connecting at least one wax gate component to a ceramic core-shell mold. The ceramic core-shell mold includes at least a filter, first core portion, a first shell portion, and at least one first cavity between the core portion and the first shell portion. The core-shell mold may manufactured using an additive manufacturing process and may include an integrated ceramic filter. At least a portion of the ceramic core-shell mold and the wax gate component is coated with a second ceramic material. The wax gate component is then removed to form a second cavity in fluid communication with the first cavity.

An investment casting process for manufacturing a cast component is provided. The investment casting process includes forming a core, casting the cast component about the core such that a core positioning feature provides a location of an anticipated pilot hole in the cast component, removing the core from the cast component once the casting is completed, locating, forming and sizing a pilot hole to form a resized pilot hole that can receive a sealing plug and installing the sealing plug into the resized pilot hole.

A parent bore cylinder block of an internal combustion, opposed-piston engine includes cooling passages that are formed using a 3-D printed casting core. The casting core can include portions that are ceramic. The parent bore cylinder block can include multiple cylinders, each cylinder with cooling passages and turbulence inducing features in those cooling passages, particularly surrounding the central portions of the cylinders.

A parent bore cylinder block of an internal combustion, opposed-piston engine includes cooling passages that are formed using a 3-D printed casting core. The casting core can include portions that are ceramic. The parent bore cylinder block can include multiple cylinders, each cylinder with cooling passages and turbulence inducing features in those cooling passages, particularly surrounding the central portions of the cylinders.

A composition for making a core for use in a moulding or casting process, a core comprising said composition, and a mould for producing an article by high pressure die casting or semi-solid casting. The composition comprises a particulate refractory material, a binder composition comprising at least one hydrophilic polymer, comprising at least one polysaccharide or polysaccharide derivative; and at least one pozzolanic additive. The mould comprises a core for defining an internal cavity of the article and the core comprises a solidified core composition. The solidified core composition comprises a particulate refractory material and a binder composition, degrades in water such that a cylinder of the solidified core composition having a maximum height of 80 mm and a maximum diameter of 50 mm disintegrates in no more than 10 minutes when immersed in water at a temperature of 20° C. and stirred at a speed of 60 rpm, and has a flexural strength of at least 300 N/cm.sup.2. The invention also resides in a method for producing an article by high pressure die casting or semi-solid casting.

A furnace for removing a molybdenum-alloy refractory metal core through sublimation comprising a retort furnace having an interior; a sublimation fixture insertable within the interior of the retort furnace, the sublimation fixture configured to receive at least one turbine blade having the molybdenum-alloy refractory metal core; a flow passage thermally coupled to the retort furnace configured to heat a fluid flowing through the flow passage and deliver the fluid to the molybdenum-alloy refractory metal core causing sublimation of the molybdenum-alloy refractory metal core.

An engine block assembly and method manufacturing an engine block assembly and related components. A casted engine block assembly includes a cylinder block portion. The cylinder block portion includes a plurality of cylinder block openings disposed therein, a cylinder block flange portion positioned at a top of the cylinder block portion and a cylinder block crankcase portion disposed at a base of the cylinder block. The cylinder block flange portion is configured for coupling the cylinder block to a cylinder head. The cylinder block portion includes a plurality of cylinder block walls extending between the cylinder block flange portion and the cylinder block crankcase portion and positioned about the plurality of cylinder block openings. The cylinder block walls house a plurality of internal channels. The plurality of cylinder block walls are void of enclosed openings extending through at least one of the cylinder block walls in the plurality of cylinder block walls.

A method of making an airfoil includes making a refractory metal core that defines an interior of the airfoil by a tomo-lithographic process, making a mold that defines an exterior of the airfoil, inserting the refractory metal core into the mold, and pouring an airfoil material between the refractory metal core and the mold to cast the airfoil.

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.