A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.

Casting method and cast manifold are provided. The method allows configuring conduits, such as conduits (46, 48) in a fuel feed boss (20) and/or a base rocket (13), which are part of the manifold for removing a ceramic core (44) from the cast without forming extraneous holes in the body of the manifold. Absence of such extraneous holes in turn allows eliminating sealing plugs and welds, which otherwise would be needed for sealing the extraneous holes.

A method of forming a component having an internal passage defined therein includes forming a precursor core having a shape corresponding to a shape of the internal passage, and forming a hollow structure around the precursor core. The method also includes removing the precursor core from within the hollow structure, and disposing an inner core within the hollow structure to form a jacketed core. The method further includes positioning the jacketed core with respect to a mold, and introducing a component material in a molten state into a cavity of the mold, such that the component material in the molten state at least partially absorbs the hollow structure from a portion of the jacketed core within the cavity. Additionally, the method includes cooling the component material in the cavity to form the component. The inner core defines the internal passage within the component.

Provided is a molding device for manufacturing a molded product having an arc-shaped bent inner space, wherein the molding device includes: a pair of molds which is joinable to each other and separable from each other, and is capable of forming a cavity C which has a shape corresponding to an outer shape of the molded product in a joined state during molding; a core which has a shape corresponding to an inner shape of the molded product, and is disposed in the inside of the cavity C which the pair of molds forms during molding; and a rotation member which is joined to a terminal end of the core, and is rotatable together with the core after molding. Compared to a conventional molding device, the molding device of the present invention becomes a molding device capable of suppressing the occurrence of a defect on a molded product having an arc-shaped bent inner space at the time of taking out the molded product.

A casting apparatus includes: a mold including a first mold segment and a second mold segment; and a transfer device that is configured to transfer a core to the first mold segment and place the core in the first mold segment, and to receive and transfer a casting. The transfer device includes a support part, a robot arm, a core grasping mechanism being provided on the support part, and a casting receiving part being provided on the support part. The transfer device is configured such that the robot arm moves the core grasping mechanism so as to place the core in the first mold segment, and moves the casting receiving part so as to receive the casting by the casting receiving part.

Described is a ceramic core for producing cast component for a gas turbine engine, the core comprising: a first cavity forming member; a second member adjacent to or opposite the first cavity forming member; and a removable web which joins the first and second members.

An engine has a cylinder block formed by a block material and defining at least one cylinder. The block defines a lubrication circuit with fluid passages including an inlet passage, a main oil gallery, a crankshaft bearing lubrication passage, and a piston ring lubrication passage. The fluid passages are formed by continuous metal walls in contact with and surrounded by the block material. At least one of the fluid passages is curved. A method of forming a component with an internal pressurized lubrication circuit includes positioning a lost core insert in a tool, with the insert shaped to form a lubrication circuit. The lost core insert has a lost core material generally encapsulated in a continuous metal shell, and at least one curved section. Material is provided into the tool to form a body surrounding the lost core insert thereby forming a component preform.

The present invention relates to an eco-mold apparatus for manufacturing a piston, a mold apparatus for manufacturing a piston, and a piston manufacturing method, which mold each part of a piston while decreasing the weight of the piston, and the apparatus may comprise: a first eco-mold part which may move forward or backward in a first direction to shape a portion of an eco-part of a piston; a second eco-mold part which may shape-match with the first eco-mold part to mold another portion of the eco-part of the piston; and a piston pickup part which picks up the piston over the second eco-mold part, so that the piston pickup part can separate the piston from the second eco-mold part.

A method of forming an airfoil (12), including: abutting end faces (72) of cantilevered film hole protrusions (64) extending from a ceramic core (50) against an inner surface (80) of a wax die (68) to hold the ceramic core in a fixed positional relationship with the wax die; casting an airfoil including a superalloy around the ceramic core; and machining film cooling holes (34) in the airfoil after the casting step to form an pattern of film cooling holes comprising the film cooling holes formed by the machining step and the cast film cooling holes (102) formed by the film hole protrusions during the casting step.

A casting mold assembly includes an airfoil defining section and a casting core. The airfoil defining section includes an outer mold wall and a direct-shelled inner mold wall. The direct-shelled inner mold wall is disposed within a forward chordwise portion of the airfoil defining section. The direct-shelled inner mold wall includes an aft end having an external radius measuring more than about 0.075 in. (1.9 mm). The casting core is secured within an aft chordwise portion of the airfoil defining section, and includes an aft end with an external radius measuring less than about 0.075 in. (1.9 mm). A cast component and a method for making the casting mold assembly are also disclosed.