1153results about "Moulding flasks" patented technology

An investment casting process wherein the wax pattern tool (42) is flexible to provide compliant support for an enclosed ceramic core (10) and to facilitate removal of the tool from the cast wax pattern (52) even when the cast shape would otherwise require multiple pull planes. Positioning pins (106) may extend from the flexible tool to make compliant contact against the core during the wax injection step. The pins may cooperate with a pedestal (128) formed on the core to support the core along multiple axes during wax injection, thereby allowing a higher wax injection pressure without damage to the core.

An investment casting pattern is formed by installing a first core to a first element of a molding die to leave a first portion of the first core protruding from the first element. After the installing, the first element is assembled with a feed core and a second element of the molding die so that the first portion contacts the feed core. A material is molded at least partially over the first core and the feed core. The first portion has one or more surface area enhancements.

An apparatus comprising a casting ring and base sized and dimensioned to be coupled together to form a cavity having one or more walls comprising an inner surface of the casting ring, having a bottom comprising an upper surface of the base, and having a form receiving member portion of the base extending into the cavity. This embodiment includes an indicator forming portion sized and positioned to form an indicator on a mold produced by at least partially filling the cavity with investment and allowing the investment to harden. In some instances the casting ring may have a lower segment sized and dimensioned to surround and receive an upper segment of the base to couple the ring and base together, wherein, the casting ring latches onto an outwardly protruding shoulder of the base when the base and casting ring are coupled together.

Pre-molding of wax or similar sacrificial material over one or more cores facilitates a subsequent molding over a core assembly. Individual cores or groups thereof may be pre-molded in a wax body. One or more such wax bodies may be assembled with other bodies and / or other cores to facilitate a main wax molding of such assembly.

An investment casting pattern is formed by forming a metallic first core element including at least one recess. The first core element is engaged to at least a mating one of an element of the die and a second core element. The recess serves to retain the first core element relative to the mating one. The die is assembled and a sacrificial material is introduced to the die to at least partially embed the first core element. The recess may be pre-formed prior to cutting the first core element from a larger sheet of material.

A core assembly including two cores is used to manufacture a blade. The first core has an outer surface shaped to complement the tip wall bottom surface. The second core has a tip surface, a side surface, and a protrusion or a depression. The tip surface is shaped to complement at least a portion of the tip wall top surface and is configured to be disposed proximate the first core. The side surface is shaped to complement at least a portion of the side wall, and the protrusion extends from the second core side surface to contact at least a portion of the ceramic mold inner surface. In embodiments employing a depression, the depression is formed in the side surface.

The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.

The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine as or stator vane, which provide a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.

A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered together at a bulb joined to the shank and radiate outwardly to integrally join different ones of the rods for increasing strength of the core.

A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.

At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.

Pre-molding of wax or similar sacrificial material over one or more cores facilitates a subsequent molding over a core assembly. Individual cores or groups thereof may be pre-molded in a wax body. One or more such wax bodies may be assembled with other bodies and / or other cores to facilitate a main wax molding of such assembly.

A method is provided for making a mold for casting advanced turbine airfoils (e.g. gas turbine blade and vane castings) which can include complex internal and external air cooling features to improve efficiency of airfoil cooling during operation in the gas turbine hot gas stream. The method steps involve incorporating at least one fugitive insert in a ceramic material in a manner to form a core and at least a portion of an integral, cooperating mold wall wherein the core defines an internal cooling feature to be imparted to the cast airfoil and the at least portion of the mold wall has an inner surface that defines an external cooling feature to be imparted to the cast airfoil, selectively removing the fugitive insert, and incorporating the core and the at least portion of the integral, cooperating mold wall in a mold for receiving molten metal or alloy cast in the mold.

The caster roll (10) is used in the manufacture of metal plate, strip, sheet, or foil. The caster roll (10) includes a cylindrical roll core (12) and at least one metal overlay (14) formed on the roll core (12). The at least one metal overlay (14) defines a plurality of cooling passages (34) for conducting a cooling medium through the at least one metal overlay (14) to cool the roll (10) during use. Additional metal overlays (16) may be formed on top of the at least one metal overlay. (14). The cooling passages (34) may also be formed in the roll core (12).

In accordance with the present invention, a casting system is provided which broadly comprises a core and a wax die spaced from said core, a refractory metal core having a first end seated within a slot in the core and a second end contacting the wax die for positioning the core relative to the wax die, and the refractory metal core having at least one of a mechanism for providing spring loading when closed in the wax die and a mechanism for mechanically locking the wax die to the core.

A method of manufacturing a turbine blade includes (a) supporting a turbine blade internal core support at opposite ends such that radially inner and outer ends of the turbine blade remain open during casting; (b) casting the blade including the airfoil portion, wherein the radially outer edge of the airfoil portion is inclined relative to horizontal; (c) machining the radially outer edge of the airfoil portion to form a peripheral shoulder about a radially outer opening in the airfoil portion; and (d) seating a tip cap on the peripheral shoulder and fixing the tip cap to the airfoil portion of the blade.

An investment casting pattern is formed by installing a first core to a first element of a molding die to leave a first portion of the first core protruding from the first element. After the installing, the first element is assembled with a feed core and a second element of the molding die so that the first portion contacts the feed core. A material is molded at least partially over the first core and the feed core. The first portion has one or more surface area enhancements.

A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.

A casting core for a turbine blade includes a plurality of rods extending above a shank. The rods define internal cooling channels in the airfoil of the blade, and the shank defines an inlet channel in the dovetail of the blade. A plurality of stubs are clustered together at a bulb joined to the shank and radiate outwardly to integrally join different ones of the rods for increasing strength of the core.

According to the prior art, through-holes in components are often introduced after the production (casting) of the component. This entails additional outlay in terms of time and equipment. The time required can be considerably shortened if a casting mold is designed in such a way that the through-hole is at least in part formed by corresponding projections being formed on the inner wall and / or the outer wall of the casting mold.

The invention relates to a method of manufacturing a brake drum by utilizing a metal-typed sand covering technique, comprising a die joint is determined by the maximum diameter position of the brake drum, a lower joint is determined by a large mouth part and an upper joint is determined by a small mouth part; an internal model and an external model are respectively arranged in order to ensure the internal profile dimension and the external profile dimension of the brake drum; an internal sand box and an external sand box are respectively arranged in order to manufacture the lower joint and the upper joint of the brake drum; after the internal model and the internal sand box, the external model and the external sand box are assembled according to prearranged clearances, the internal sand box and the external sand box are covered with sands through a sand injection hole; metal liquid is poured after the internal sand box and the external sand box with sand cover are tightly locked. The invention has the advantages of improving working environment, more precise dimension of the castings, better surface quality, higher yield, lower cost and higher production efficiency.

The invention relates to a vacuum sealed molding casting method production process for a front bridge and a rear bridge of an automobile. The front bridge and the rear bridge of the automobile are characterized by being produced by the following steps that: (1) a model is provided with a longitudinal air hole by which the model is divided into an upper half body and a lower half body; (2) the upper half body of the model is flatly placed on an air exhaust box, a film is roasted to be soft and then covered on the surface layer of the model, and after air exhaust, the film is closely adhered to the model and a top plate; (3) the film, covered on the circumference of the gating and risering model, is jointed with an in gate in the half body of the model, the film on the model is sprayed with a coating, and then a sand box is covered, the sand box is filled with dry sand, a vibrating table is started to tamp the dry sand, the surface of the sand layer is scraped to be smooth, and an upper opening is covered by a sealing cover; (4) the dry sand is agglomerated and hardened by vacuum pumping, the air exhaust box stops air exhaust, but the sand box is continuously vacuumized, the sand box is lifted up, the upper half body models is taken out, the gating and risering model is drawn out, and the upper sand box is formed; (5) the lower half body of the model repeats the steps to form the lower sand box; and (6) the bottom surfaces, where the mould cavities of the half body models are formed, of the upper sand box and the lower sand box are closed, and the molten metal is poured in from the gating and risering, and after cooling, the blanks of the front bridge and the rear bridge of the automobile are produced. The products produced by the process are high in accuracy and low in cost.

A sacrificial core for forming an interior space of a part includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

Articles for use with highly reactive alloys that include a graphite crucible having an interior, and at least a first protective layer applied to the interior of the graphite crucible in which the graphite crucible having the first protective layer is used for melting highly reactive alloys.

A method involves forming a core assembly. The forming includes molding a first ceramic core over a first refractory metal core to form a core subassembly. The subassembly is assembled to a second ceramic core.

A method of manufacturing a catalyst, a catalyst precursor, or a catalyst support comprising: (a) mixing a refractory metal oxide or precursor thereof with a liquid to form a paste; (b) adding said paste to an extruder, the extruder having a die plate comprising one or more dies, each die having a plurality of apertures, the outlet of each aperture having a cross sectional area of 6 mm2 or less; (c) extruding the paste through the apertures to form catalyst support extrudates;wherein the inlet of the apertures has a greater cross sectional area than the outlet of said apertures; and wherein for at least one die the combined cross sectional area of all apertures at the inlet relative to the total cross sectional area of the die at the inlet is higher than 50%.