Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mold in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron having first and second sides (30a, 30b) and third and fourth sides (30c, 30d), in which the third and fourth sides extend between the first and second sides, flaring apart from the first side towards the second side, first at a first angle and subsequently at a second larger angle, and said at least one part is machined in the blank.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mold in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

Abstract: The invention concerns a unit comprising a mold (4) adapted to receive a molten metal alloy and the said metal alloy poured therein. The alloy is TiAl. The mold is rotational and comprises receiving recesses (135) made of steel, metal alloy and/or ceramic, and, at the location of a plurality of section planes each passing through the mold and the poured metal alloy, the mold has a surface heat capacity less than that of the poured metal alloy.

Abstract: The invention relates to the field of monocrystalline casting, and more specifically to a mold (1) for monocrystalline casting, and also to fabricating and using the mold. In particular, the mold (1) presents a mold cavity (7) comprising a first volume (7a), a second volume (7b) and a grain duct (4). The second volume (7b) is situated on the first volume (7a), being in communication therewith, and includes at least one horizontal projection relative to the first volume (7a). The grain duct (4) has a bottom end (4a) connected to the first volume (7a) and a top end (7b) adjacent to said horizontal projection of the second volume (7b). The mold (1) also has a separator member (11) interposed between the second volume (7b) of the mold cavity (7) and the top end (4b) of the grain duct (4).

Abstract: A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.

Abstract: A field of casting, and more particularly to a shell mold, and also to methods of fabricating and using such a shell mold. This shell mold includes a central cylinder, a plurality of molding cavities arranged in an assembly around the central cylinder, and at least one heat shield that is substantially perpendicular to the main axis. The central cylinder extends along a main axis between a casting cup and a base. Each molding cavity is connected to the casting cup by at least one feed channel, and also, by a baffle-selector with a starter in the base. The at least one heat shield completely surrounds each molding cavity in a plane that is substantially perpendicular to the main axis.

Abstract: A casting pattern for a lost-pattern casting, the pattern being in a shape of a turbine engine blade with a root and a body on either side of a platform that is substantially perpendicular to a main axis of the blade, and a method of producing a shell mold from the pattern, and a casting method using the shell mold. The blade body presents a pressure side, a suction side, a leading edge, and a trailing edge. The pattern also includes an expansion strip adjacent to the trailing edge, and a refractory core embedded in the pattern but presenting, both on the pressure side and on the suction side, a respective flush varnished surface between the trailing edge and the expansion strip. A web extends between the platform and the expansion strip and presents a free edge between them.

Abstract: The invention relates to the field of monocrystalline casting, and more specifically to a mold (1) for monocrystalline casting, and also to fabricating and using the mold. In particular, the mold (1) presents a mold cavity (7) comprising a first volume (7a), a second volume (7b) and a grain duct (4). The second volume (7b) is situated on the first volume (7a), being in communication therewith, and includes at least one horizontal projection relative to the first volume (7a). The grain duct (4) has a bottom end (4a) connected to the first volume (7a) and a top end (7b) adjacent to said horizontal projection of the second volume (7b). The mold (1) also has a separator member (11) interposed between the second volume (7b) of the mold cavity (7) and the top end (4b) of the grain duct (4).

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

Abstract: The invention concerns a unit comprising a mould (4) adapted to receive a molten metal alloy and the said metal alloy poured therein. The alloy is TiAl.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron having first and second sides (30a, 30b) and third and fourth sides (30c, 30d), in which the third and fourth sides extend between the first and second sides, flaring apart from the first side towards the second side, first at a first angle and subsequently at a second larger angle, and said at least one part is machined in the blank.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

Abstract: The invention relates to the field of monocrystalline casting, and in particular to a mold (1) for monocristalline casting comprising at least a molding cavity (7), a starter cavity (10) having at least a first volume (10a) in the form of an upside-down funnel, and a distinct second volume (10b) forming a plinth at the bottom of the first volume and projecting perceptibly relative to said first volume in at least one horizontal direction, a selector channel (9) connecting said starter cavity (10) to said molding cavity (7), and a support rod (20) that is laterally offset relative to said selector channel, and that connects the second volume (10b) of the starter cavity (10) to the molding cavity (7). The invention also provides a casting method using such a mold (1).

Abstract: The invention relates to the field of monocrystalline casting, and in particular to a mold (1) for monocristalline casting comprising at least a molding cavity (7), a starter cavity (10) having at least a first volume (10a) in the form of an upside-down funnel, and a distinct second volume (10b) forming a plinth at the bottom of the first volume and projecting perceptibly relative to said first volume in at least one horizontal direction, a selector channel (9) connecting said starter cavity (10) to said molding cavity (7), and a support rod (20) that is laterally offset relative to said selector channel, and that connects the second volume (10b) of the starter cavity (10) to the molding cavity (7). The invention also provides a casting method using such a mold (1).

Abstract: A casting pattern for a lost-pattern casting, the pattern being in a shape of a turbine engine blade with a root and a body on either side of a platform that is substantially perpendicular to a main axis of the blade, and a method of producing a shell mold from the pattern, and a casting method using the shell mold. The blade body presents a pressure side, a suction side, a leading edge, and a trailing edge. The pattern also includes an expansion strip adjacent to the trailing edge, and a refractory core embedded in the pattern but presenting, both on the pressure side and on the suction side, a respective flush varnished surface between the trailing edge and the expansion strip. A web extends between the platform and the expansion strip and presents a free edge between them.

Abstract: A field of casting, and more particularly to a shell mold, and also to methods of fabricating and using such a shell mold. This shell mold includes a central cylinder, a plurality of molding cavities arranged in an assembly around the central cylinder, and at least one heat shield that is substantially perpendicular to the main axis. The central cylinder extends along a main axis between a casting cup and a base. Each molding cavity is connected to the casting cup by at least one feed channel, and also, by a baffle-selector with a starter in the base. The at least one heat shield completely surrounds each molding cavity in a plane that is substantially perpendicular to the main axis.

Abstract: A process for manufacturing a single-crystal turbomachine nozzle guide vane including an airfoil between two platforms is disclosed. The process includes pouring molten metal into a shell mold followed by directional solidification from a single crystal provided by a single-crystal grain provider device placed in the mold and having a predetermined orientation coinciding with the vertical. The volumes of the mold forming the platforms are oriented in a plane parallel to the vertical direction of the single crystal. The single-crystal grain providing device emerges in a grain duct forming a connection between the device and the lower ends of the platforms. The grain duct is shaped to present two branches for feeding the platforms and a web-shaped volume extending between the feed branches, the platforms and a lower edge of the airfoil. The upper edge of the volume forming the airfoil is inclined to the horizontal direction.

Abstract: The present invention relates to a process for manufacturing a single-crystal turbomachine nozzle guide vane comprising an airfoil between two platforms, by pouring molten metal into a shell mold followed by directional solidification, the front of which advances vertically upward, from a single crystal provided by a single-crystal grain provider device placed in the lower portion of the mold and having a predetermined orientation, the [001] direction coinciding with the vertical, the volumes of the mold forming the platforms being oriented in a plane parallel to the [001] direction of said single crystal and the volume of the mold forming the airfoil comprising a lower edge, the device providing the single-crystal grain emerging in a grain duct forming a connection between said device and the lower ends of the platforms, the grain duct being shaped so as to comprise two branches for feeding the platforms and a web-shaped volume extending between said feed branches, the platforms and the lower edge of the air

Abstract: A method of manufacture of a multilayer ceramic shell mould whereof at least one contact layer out of a wax master pattern or a part to be manufactured, or other similar material, includes a step of preparing a first slip containing ceramic particles and a binder; a step of dipping the master pattern in a first slip; a step of forming the contact layer, and a step of depositing sand particles particles onto the layer and drying the contact layer. The ceramic particles of the slip are mullite particles and the slip includes a texturing agent.