Abstract: What is described is the use of a particulate material comprising, as its sole constituent or as one of multiple constituents, a particulate synthetic amorphous silicon dioxide having a particle size distribution with a median in the range from 0.1 to 0.4 ?m, determined by means of laser scattering, as additive for a molding material mixture at least comprising: a refractory mold base material having an AFS grain fineness number in the range from 30 to 100, particulate amorphous silicon dioxide having a particle size distribution with a median in the range from 0.7 to 1.5 ?m, determined by means of laser scattering, and water glass, for increasing the moisture resistance of a molding producible by hot curing of the molding material mixture. Also described are corresponding processes, mixtures and kits.

Abstract: The invention relates to a method for producing a helical metal body (1, 1?), in particular made of aluminum or an aluminum alloy. A blank is first produced in a primary shaping process, a metal forming process, or in a removal process, in particular a machining process, and one or more recesses (100, 101, 201, 202, 203) are then introduced into the blank using a removal process, said recesses defining a circumferential coil, the adjacent windings thereof being mutually spaced, in particular electrically insulated from one another.

Abstract: A method for manufacturing a turbine shroud segment with at least one undercut region. The method includes forming a removable insert including an external surface corresponding to at least a portion of a wall of the undercut region in the turbine shroud segment; placing the removable insert in a mold including a mold cavity corresponding to a shape of the turbine shroud segment; injecting a metal injection molding (MIM) feedstock into the mold cavity and around the removable insert to form a shroud green body with the at least one undercut region; and, sintering the shroud green body to form the shroud body.

Abstract: The present disclosure discloses a production line for ceramic shell making and a method for ceramic shell making. The production line may include a conveyor chain system, a robotic arm, a slurry coating device, and a sanding device. The conveyor chain system may be configured to convey a batch of modules. The robotic arm may be configured to replace and remove one or more modules among the batch of modules relative to the conveyor chain system and hold the one or more modules during a plurality of subsequent operations. The robotic arm may be configured to be moveable to a plurality of positions each of which corresponds to one of a plurality of stations. The slurry coating device may be configured to coat the one or more modules in slurry. The sanding device may be configured to sand the one or more modules.

Abstract: A method to produce a ceramic matrix composite part, wherein the method comprises providing a ceramic fiber preform. Wherein the ceramic fiber preform includes a three-dimensional framework of a plurality of ceramic fibers. The method comprising, prior to melt infiltration, adding a layer of machinable stock to a target area of the ceramic fiber preform, melt infiltrating the ceramic fiber preform, forming the ceramic matrix composite part by cooling the melt infiltrated ceramic fiber preform, and machining the part in the target area where the machinable stock is located.

Abstract: A casting core for casting moulds can include a central core and a core shroud arranged around the central core. The core shroud containing contains or consists of ceramic particles bound to a binder. The central core contains ceramic particles bound to a binder, wherein the ceramic particles of the central core contain at least one component, which exhibits, at a temperature in a range from 100° C. to 1500° C., a thermally induced phase transformation, and/ or at least two components, the thermal expansion coefficients of which at 20° C. differ by at least 5·10?6K?1.

Abstract: A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first passage core. The first passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

Abstract: A core for the foundry of an aeronautical part such as a turbine blade, the core being intended to be disposed in an inner housing defined by a mold, the core comprising a body intended to form the internal shape of the turbine blade, an impact portion, disposed on at least a portion of the periphery of the body so as to break a fluid jet when filling the inner housing with the fluid, the impact portion comprising a top and at least one deflection wall converging towards the top.

Abstract: Provided is a multicore. The multicore includes a first core, being made of a water-insoluble material, having a hollow formed in the first core and, having an opening formed at both ends of the first core and connected to the hollow, a second core, being made of a water-soluble material and disposed inside the hollow, and a coating layer, being configured to surround the first core to prevent at least a portion of the first core and the second core from being exposed to an outside. Further, the first core includes a plurality of spaces to allow a fluid supplied to an interior of the first core to flow toward the second core.

Abstract: Disclosed herein is a casting core for casting molds, the casting core comprising an inner core and an outer core arranged around the inner core. The outer core contains or consists of ceramic particles bound with a binder. The inner core contains ceramic particles bound with a binder and additionally one or more placeholder elements. The placeholder element(s) is/are at least partially thermally decomposable. Also disclosed is a method for producing the casting core and use of the casting core.

Abstract: Disclosed is a preparation method of a foamed aluminum special-shaped part. The preparation method comprises the following steps: S1, pressing wax molds; S2, making a shell; S3, carrying out smelting; S4, carrying out casting; and S5, vibrating the shell. Finally, the foamed aluminum special-shaped part is obtained for a preparation process of a foamed aluminum compound casting.

Abstract: A system for making a hybrid cam bore sand core with metal chills for an engine block includes an engine block cast of an aluminum material. A camshaft bore extends through the engine block. A cam bore sand core with at least one metal chill is positioned within the camshaft bore. A body portion of the at least one metal chill is positioned in direct contact with a cam bearing surface of at least one cam bearing member during casting of the engine block to increase a cooling rate of the at least one cam bearing member and create a crystalline material depth of the cam bearing member having enhanced mechanical properties.

Abstract: A method of bonding a mini-core to a surface of a core is provided. The method includes providing the mini-core with an attachment device that includes a protrusion of a surface of the mini-core, dipping the protrusion into a supply of paste to transfer a fixed quantity of paste to the protrusion and affixing the protrusion to the surface of the core with the fixed amount of paste interposed between the surface and the protrusion.

Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.

Abstract: A hollow turbomachine turbine blade including rising cavities communicating with a squealer tip of the blade through standard dust removal holes intended to remove dust and through inclined cooling bores intended to cool a barrier of the squealer tip by leading to a pressure side face of the blade, at least one rising cavity including a tip with no dust removal hole and an inclined cooling bore formed in its lateral wall and intended to cool the squealer tip barrier is enlarged to have a diameter at least equal to the standard diameter of a dust removal hole and thus also serve as a dust removal hole, so that the air flow extracted for cooling the blade is reduced, at least one of the cavities positioned facing the tip of one of the rising cavities having an increased volume corresponding to at least a volume deducted from the tip of the rising cavity.

Abstract: Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the least the ceramic core serves as a build surface for a subsequent process of additively manufacturing the tip portions. The build surface is created by removing a top portion of the airfoil and the core, or by placing an ultra-thin shim on top of the airfoil and the core. The overhang projected by the shim is subsequently removed. These methods are not limited to turbine engine applications, but can be applied to any metallic object that can benefit from casting and additive manufacturing processes. The present disclosure also relates to finished and intermediate products prepared by these methods.

Abstract: A vibration-type driving apparatus is capable of, in a case where a sintered body is impregnated with resin, preventing the resin that has hardened from interfering with other members. A movable body is brought into pressure contact with a vibrating body having an electro-mechanical energy conversion element and an elastic body. The vibrating body and the movable body are moved relatively to each other through vibrations excited in the vibrating body. The movable body has a frictional surface including the sintered body impregnated with the resin and comes into contact with the vibrating body. The movable body has a sloped surface adjacent to the frictional surface in a cross section perpendicular to a direction in which the vibrating body and the movable body move relatively to each other. An angle formed by the frictional surface and the sloped surface is greater than 90 degrees and less than 180 degrees.

Abstract: A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

Abstract: 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.

Abstract: 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.

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

Abstract: A mold for manufacturing a casted workpiece is, at least in-part, manufactured utilizing an additive manufacturing process. The mold may have a core having non-line-of-sight features that are additively manufactured and in contact with an outer shell of a wax mold and/or an outer shell of a casting mold of the mold. The outer shell of either the wax or casting molds may also be additively manufactured, and the shell of the casting mold may be additively manufactured as one unitary piece to the core.

Abstract: A method for fabricating a cast component with a cooling channel is provided. The method includes forming a shell mold over a pattern-ceramic matrix composite (CMC) elongated core arrangement to define a cavity in the shell mold. The pattern-CMC elongated core arrangement includes a pattern-forming material with a CMC elongated core disposed therein. The pattern-forming material in the cavity is replaced with metal via a casting process to form the cast component with the CMC elongated core disposed therein defining the cooling channel. The CMC elongated core is removed from the cast component to open the cooling channel for fluid communication.

Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.

Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

Abstract: A core assembly includes a core that includes an exterior surface that has a recessed area that extends along the exterior surface. An insert includes a contact surface that corresponds to the recessed area.

Abstract: A cast cylinder block for an internal combustion engine includes a first and a second cylinder bore and a shared bore wall. The first cylinder bore includes a first bore wall and the second cylinder bore includes a second bore wall. The shared cylinder bore wall includes a first portion and a second portion. A portion of the first bore wall combines with a portion of the second bore wall to form the shared cylinder bore wall. The first portion of the shared bore wall is an as-cast portion. The second portion of the shared bore wall is a metal matrix composite.

Abstract: A ceramic structure may include a sacrificial ceramic core. The sacrificial ceramic core may include a ceramic body corresponding to a cooling cavity of a heat exchanger segment. The ceramic body may have an exterior surface that includes an outer surface and an inner surface interconnected to one another by at least a leading edge, a trailing edge, a tip facing edge and a base facing edge. The ceramic body may define a plurality of apertures extending between the outer surface and the inner surface. The ceramic body may include a trailing first pin and a leading first pin. The trailing first pin and the leading first pin may extend away from the inner surface. The leading first pin may be spaced away from the trailing first pin and in closer proximity to the leading edge than the trailing first pin.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage extending between a root and a tip of the airfoil. The airfoil further defines a pocket positioned between the cooling passage and an exterior surface of the airfoil and spaced apart from the cooling passage and the exterior surface. The pocket provides a thermal impediment between the cooling passage and the exterior surface of the airfoil.

Abstract: A ceramic core used for fabricating a hollow turbine blade for a turbine engine using the lost wax casting technique, the blade including calibrated dust-removal holes emanating from a top of at least one cavity and opening out into a bathtub of the blade, wherein each of the calibrated dust-removal holes is formed in a core portion of height that is determined to be sufficient to guarantee mechanical strength, the core portion including a through orifice of axis perpendicular to a longitudinal axis of the calibrated dust-removal hole and defining on either side of the through orifice firstly a core cylinder having a determined diameter corresponding to the dust-removal hole that is to be formed, and secondly a remaining core volume that is to be plugged after casting, such that the calibrated dust-removal hole is obtained without drilling and without using connection rods.

Abstract: A method for manufacturing a turbine engine blade (25) comprising a pressure side and a suction side separated from one another by an inner space for the circulation of cooling air, the blade (25) comprising a tip (S) with a closing wall (29) joining the pressure side and suction side walls in the region of this tip (S) in order to define a well shape, the closing wall including through-holes. The closing wall (29) obtained by moulding has a considerable nominal thickness with pits (36, 37) locally reducing this thickness at each through-hole in order to facilitate the removal by chemical etching of alumina rods defining the holes. Since the closing wall (29) thus has a large nominal thickness, it can then be machined in order to form raised patterns or complex shapes inside the well.

Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom, the core assemblies having a leading edge hybrid skin core positioned relative to a plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil. The leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.

Abstract: A method locates and maintains a core in fixed space relationship within the interior of a shell mould. The method provides at least one pin extending into the core with at least one axial end of the pin protruding from the core. A wax pattern having an outer surface is formed by encasing the core and at least one protruding axial end of the pin in wax such that at least one protruding axial end of the pin terminates at the outer surface of the wax pattern. A shell mould is formed around the wax pattern such that, upon removal of the wax pattern, and in a subsequent casting process for production of hollow metal components, at least one protruding axial end of the pin abuts the shell mould, thus fixing the pin and maintaining a position of the core relative to the mould. The protruding axial end of the pin has an enlarged head.

Abstract: A method of forming a component includes the steps of placing a core into a mold and pouring a component material around the core. The component material is allowed to solidify. The core is then removed from within the material, leaving a component having at least a first and a second cavity formed by the core. A first filler material is moved into the first cavity, and a second filler material is moved into the second cavity. The component is inspected for the presence of an apparent residual core within the first cavity and the second cavity. The location is identified of the apparent residual core from the core based upon an identification of whether the location of the apparent residual core is in the first or second filler materials. A method of inspecting a component formed by investment casting is also disclosed.

Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.

Abstract: A core assembly for forming a cast component includes a refractory metal core and a ceramic core element. The refractory metal core includes first and second ends and sides extending from the first end to the second end. The ceramic core element includes a slot positioned between first and second lands, each land having an inner surface facing the slot and an adjacent outer surface. The first end of the refractory metal core is secured within the slot with an adhesive, and the refractory metal core extends from the ceramic core element in both a longitudinal and a transverse direction. The slot, lands, and refractory metal core form a core assembly providing access paths to the sides of the refractory metal core. Surplus adhesive is removed from the refractory metal core via the access paths. Investment casting provides the component with an internal passage and an internal cooling circuit.

Abstract: A method for the production of castings which are permanently provided with readable information. An identification element, which has an information surface, provided with information, and a casting surface which is assigned to the casting and also provided with information, is arranged on a casting mould surface assigned to a mould cavity of a casting mould so that the information surface is covered, while the casting surface is exposed in the mould cavity. A metal melt is poured into the mould, so that, during casting or solidification of the metal melt, a firmly bonded, form-fit or force-fit connection of the identification element to the casting is produced. The information on the casting surface is reproduced in the manner of a stamp on surface of the casting. The casting is then removed from the mould and fettled.

Abstract: There is provided a manufacturing method including: forming a molded body element with a molding material containing a ceramic powder and a binder; forming a ceramic molded body by disposing at least one molded body element in a mold and then injecting a molding material containing a ceramic powder and a binder into the mold and graft molding a graft molded body element to the molded body element; and forming a ceramic sintered body by degreasing and sintering the ceramic molded body. A graft connecting surface of the molded body element to which the graft molded body element is graft molded is formed so as to have a surface roughness of 2 ?m or more in terms of Ra.

Abstract: A gas turbine engine blade includes a platform arranged between a root and an airfoil. A cooling passage extends from the root through the platform to the airfoil. The cooling passage includes an inlet that splits into first and second branches that rejoin one another in a platform passage arranged in the platform. An airfoil passage extends from the platform passage and is arranged in the platform.

Abstract: A ceramic core is obtained by firing a mixture that contains 0.1-15.0% by mass of alumina and 0.005-0.1% by mass of potassium and/or sodium with the balance made up of silica and unavoidable impurities. Not less than 90% by mass of amorphous silica is contained in 100% by mass of the silica. A method for producing a ceramic core, wherein: a blended material is obtained by blending 25-45% by volume of a binder into 55-75% by volume of a mixture that is obtained by mixing alumina, potassium and/or sodium, and silica so as to have the above-mentioned composition; the blended material is injected into a die so as to obtain a molded body; and the molded body is degreased at 500-600° C. for 1-10 hours, and then fired at 1,200-1,400° C. for 1-10 hours.

Abstract: 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.

Abstract: Provided in an embodiment is a method for molding, including: providing a molten alloy in a space between a mold cavity and an etchable block shaped to form an undercut on a part formed in the space, cooling the molten alloy to form the part with the undercut, and etching the etchable block. An undercut is a beveled edge caused by an etchant attacking an etchable block laterally and optionally vertically. The formed part can be made of a bulk amorphous alloy. In some cases, the etchable block can also be used to form at least one threaded portion in the part.

Abstract: A method of forming a cast product (30) by providing a core (52) having a plurality of sections (54) and one or more gaps (55) there-between. The core further includes an insert member (60) spanning the gap (55) between adjacent sections (54). The core (52) is located within a mold (68) and a liquid phase material is introduced into gap (55) between the core sections. The liquid phase material is solidified in the gap so as to form a cast feature of a resulting solid product and the core sections (54) are removed from the solid product (30) such that the insert member (60) remains securely held within the feature (74).

Abstract: The invention relates to a method for producing casting molds and cores, in which a foundry base material comprising at least one refractory material and a binder curable by CO2, preferably based on water glass, is cured by gassing with CO2 and flushing with a second gas. The invention further relates to molds and cores produced according to this method.

Abstract: A multi-wall gas turbine airfoil (192) and method of forming same using a casting core (150) having a monolithic body configured to define a pressure side wall (12), a suction side wall (14), and a third wall (16). The casting core is formed around a fugitive insert (96) during a single pour casting process.

Abstract: A composite core for forming a passage in an investment casting mold is provided including a core element. A generally hollow structural element is positioned about an exterior of the core element. The structural element is configured to deform when a force is applied to the structural element. A rigid shell element is integrally formed about the structural element. The shell element is configured to break when the structural element deforms.

Abstract: A multi-wall ceramic core for casting an airfoil with one or more internal cooling passages is made by preforming at least one fugitive core insert to have a joint-forming surface with a male and/or female joint feature and then forming at least one fugitive core insert in-situ adjacent and integrally connected and fused to the at least one preformed core insert at the joint-forming surface to form an interlocked, fused joint to form a composite core insert that includes features to form internal passage surfaces in the core when the composite core insert is removed. Another aspect involves preforming first and second fugitive core inserts to have respective joint-forming surfaces with respective snap-fittable joint features and assembling the first and second fugitive core inserts to form a composite core insert by snap fitting the snap-fittable joint features together to form an interlocked joint.

Abstract: Disclosed is a cast pin equipped with circular grooves which are provided at any location. The cast pin (10) is equipped with: an outer tube (11) in the shape of a hollow body the tip of which is closed; an inner tube (20) inserted into the outer tube (11); and a cooling medium pipe (30) that is inserted into the inner tube (20) and supplies a cooling medium to the interior of the inner tube (20). Three circular grooves (22) are formed at prescribed intervals in the longitudinal direction, for example, on the outer circumferential surface (21) of the inner tube (20). The circular grooves (22) are formed in the outer circumferential surface (21) by applying a cutting tool from the radial outward direction of the inner tube (20).

Abstract: The disclosure relates generally to core compositions and methods of molding and the articles so molded. More specifically, the disclosure relates to core compositions and methods for casting hollow titanium-containing articles, and the hollow titanium-containing articles so molded.