Abstract: The invention relates to a method for determining the position of the cores in an injection mould, comprising the steps essentially consisting of: selecting a core Rrep in a population of cores with the least difference from the mean of the measured differences between k cores and the theoretical three-dimensional spatial model, positioning this core Rrep in space relative to at least one of the functional faces of a theoretical three-dimensional spatial model of the core, and repositioning core support points so that they can support the core Rrep in the position corresponding to its repositioning in space performed in the previous step.

Abstract: The invention relates to a method for determining the position of the cores in an injection mould, comprising the steps essentially consisting of: selecting a core Rrep in a population of cores with the least difference from the mean of the measured differences between k cores and the theoretical three-dimensional spatial model, positioning this core Rrep in space relative to at least one of the functional faces of a theoretical three-dimensional spatial model of the core, and repositioning core support points so that they can support the core Rrep in the position corresponding to its repositioning in space performed in the previous step.

Abstract: The present invention relates to a method for machine finishing the shape of a blank casting for a multi-vane, in particular bi-vane, nozzle of a turbine engine, comprising a first vane and a second vane extending substantially in a radial direction between two walls that are radially inner and radially outer, respectively, the suction face of the first vane defining, together with the pressure face of the trailing edge of the second vane, a cross section of flow (SP), the method comprising measuring, by means of probing, the position of predefined points on said respectively radially inner and radially outer walls on the surface of the vanes and calculating the machining allowances (?1 and ?2 respectively) on the first and second vanes with respect to the theoretical profile at said points, wherein the method comprises calculating said cross section of flow (SP) from the height of the duct between said radially inner and radially outer walls, and values of the machining allowances (?1 and ?2), a correction o

Abstract: The invention relates to a method for determining the position of the cores in an injection mould, comprising the steps essentially consisting of: selecting a core Rrep in a population of cores with the least difference from the mean of the measured differences between k cores and the theoretical three-dimensional spatial model, positioning this core Rrep in space relative to at least one of the functional faces of a theoretical three-dimensional spatial model of the core, and repositioning core support points so that they can support the core Rrep in the position corresponding to its repositioning in space performed in the previous step.

Abstract: The present invention relates to a method for machine finishing the shape of a blank casting for a multi-vane, in particular bi-vane, nozzle of a turbine engine, comprising a first vane and a second vane extending substantially in a radial direction between two walls that are radially inner and radially outer, respectively, the suction face of the first vane defining, together with the pressure face of the trailing edge of the second vane, a cross section of flow (SP), the method comprising measuring, by means of probing, the position of predefined points on said respectively radially inner and radially outer walls on the surface of the vanes and calculating the machining allowances (?1 and ?2 respectively) on the first and second vanes with respect to the theoretical profile at said points, wherein the method comprises calculating said cross section of flow (SP) from the height of the duct between said radially inner and radially outer walls, and values of the machining allowances (?1 and ?2), a correction o

Abstract: A shell mold for manufacturing aircraft turbomachine bladed elements using a lost wax molding technique, including: shell mold bladed elements including a blade portion located between a first end part delimiting an impression of a platform and a second end part delimiting an impression of another platform, with the blade portion including a trailing edge zone; a metal feeder having a central axis around which the bladed elements are distributed; and one or a plurality of screens that form heat accumulators arranged in a shell mold interior space, across from inwardly directed trailing edge zones.