Abstract: A method for making a wax model for the manufacture of a part, the part including at least one cavity, the method including: arranging at least two core elements made of a ceramic material into a wax mold, the core elements having at least partially a shape complementary to the cavity of the part to be manufactured, and injecting wax into the wax mold, around the core elements, so as to form the wax model, the two core elements being assembled prior to the injection of wax by at least one staple, the staple including a central portion from which two branches extend, each branch being fitted into an orifice formed in one of the core elements.

Abstract: A method for making a wax model for the manufacture of a part, the part including at least one cavity, the method including: arranging at least two core elements made of a ceramic material into a wax mold, the core elements having at least partially a shape complementary to the cavity of the part to be manufactured, and injecting wax into the wax mold, around the core elements, so as to form the wax model, the two core elements being assembled prior to the injection of wax by at least one staple, the staple including a central portion from which two branches extend, each branch being fitted into an orifice formed in one of the core elements.

Abstract: A method is for positioning a hollow workpiece obtained by casting and that enables the workpiece obtained in this way to be machined in accurate manner. The workpiece is obtained by a casting method involving a mold and a sacrificial core inserted inside the mold and serving to form at least one cavity in the workpiece. The workpiece includes surfaces of a first type defined during casting by the surfaces of the mold, and surfaces of a second type defined during casting by the surfaces of the core. A frame of reference for positioning the workpiece is constructed that includes at least three reference points (P1-P3) belonging to surfaces of the second type of the workpiece.

Abstract: An assembly for manufacturing a wax moulding of a turbine engine blade has a wax injection mould in which a core is able to be mounted in a predetermined moulding position, the core including a main element and at least a first secondary element each including at least one functional part and a non-functional part, wherein the non-functional part of the first secondary element includes a rod portion extending in a longitudinal direction of the blade and housed in a first slot of the non-functional part of the main member, the mould including a first internal boss clamping said rod portion at the bottom of the first slot.

Abstract: The invention provides a method of assembling together a first core (12) and a second core (14) in order to make a non-permanent model configured for use in lost wax molding to form a part having a first cavity and a second cavity corresponding respectively to the first core and to the second core. The invention is characterized by the fact that the first and second cores (12, 14) are assembled together with a first spacer (20), the first spacer (20) being arranged between the first and second cores.

Abstract: A method of making a multi-vane model for a nozzle guide out of sacrificial material, includes the steps of fabricating a single-vane model out of sacrificial material, assembling at least two sacrificial material single-vane models with each other, and positioning (104, 108) a holder element on at least one sacrificial material single-vane model so as to hold a predetermined spacing between an inner platform and an outer platform. An assembly of a sacrificial material single-vane model for a nozzle guide together with a holder element, and also an assembly of a sacrificial material multi-vane model for a nozzle guide together with a holder element.

Abstract: The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.

Abstract: A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.

Abstract: A shell mold for a guide vane sector includes a first platform and a second platform that are mutually coaxial and between which there extends at least one airfoil. The shell mold has a first platform molding portion suitable for forming the first platform, a second platform molding portion suitable for forming the second platform, an airfoil molding portion suitable for forming the airfoil, a fastener molding portion suitable for forming a fastener projecting from the first platform towards a first edge of the first platform, a main casting duct, a distribution duct connecting the main casting duct to the fastener molding portion, and an auxiliary duct connecting the main casting duct to the first platform molding portion beside said first edge.

Abstract: The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.

Abstract: A method of making a multi-vane model for a nozzle guide out of sacrificial material, includes the steps of fabricating a single-vane model out of sacrificial material, assembling at least two sacrificial material single-vane models with each other, and positioning (104, 108) a holder element on at least one sacrificial material single-vane model so as to hold a predetermined spacing between an inner platform and an outer platform. An assembly of a sacrificial material single-vane model for a nozzle guide together with a holder element, and also an assembly of a sacrificial material multi-vane model for a nozzle guide together with a holder element.

Abstract: The invention provides a method of assembling together a first core (12) and a second core (14) in order to make a non-permanent model configured for use in lost wax molding to form a part having a first cavity and a second cavity corresponding respectively to the first core and to the second core. The invention is characterized by the fact that the first and second cores (12, 14) are assembled together with a first spacer (20), the first spacer (20) being arranged between the first and second cores.

Abstract: A method is for positioning a hollow workpiece obtained by casting and that enables the workpiece obtained in this way to be machined in accurate manner. The workpiece is obtained by a casting method involving a mold and a sacrificial core inserted inside the mold and serving to form at least one cavity in the workpiece. The workpiece includes surfaces of a first type defined during casting by the surfaces of the mold, and surfaces of a second type defined during casting by the surfaces of the core. A frame of reference for positioning the workpiece is constructed that includes at least three reference points (P1-P3) belonging to surfaces of the second type of the workpiece.

Abstract: A core used in the manufacture, by lost-wax casting, of a turbomachine blade, includes a main element and at least one first secondary element, each including a functional part and a non-functional part. The non-functional part of the main element and the non-functional part of the at least one first secondary element are assembled and shaped so as to cooperate with each other by sliding in a longitudinal direction extending between the base and the top of a blade and by rotating around the longitudinal direction.

Abstract: An assembly for manufacturing a wax moulding of a turbine engine blade has a wax injection mould in which a core is able to be mounted in a predetermined moulding position, the core including a main element and at least a first secondary element each including at least one functional part and a non-functional part, wherein the non-functional part of the first secondary element includes a rod portion extending in a longitudinal direction of the blade and housed in a first slot of the non-functional part of the main member, the mould including a first internal boss clamping said rod portion at the bottom of the first slot.

Abstract: A shell mold (100) for a guide vane sector comprising a first platform and a second platform that are mutually coaxial and between which there extends at least one airfoil, the shell mold having a first platform molding portion (112) suitable for forming the first platform, a second platform molding portion (114) suitable for forming the second platform, an airfoil molding portion (116) suitable for forming the airfoil, a fastener molding portion (118) suitable for forming a fastener projecting from the first platform towards a first edge of the first platform, a main casting duct (120), a distribution duct (122) connecting the main casting duct (120) to the fastener molding portion (118), and an auxiliary duct (124) connecting the main casting duct (120) to the first platform molding portion (112) beside said edge.