Abstract: A method for separating a part blank from a support, wherein the support and the part blank are manufactured by additive manufacturing. The support includes an inner cavity containing a fluid. The separation method includes a heating of the support to deform the support by fluid expansion in the inner cavity until the support is separated from the part blank.

Abstract: A method for holding a part blank inside a holding assembly. The holding assembly includes a first holding portion. The first holding portion includes an inner cavity containing a fluid. The part blank and the first holding portion are at least partially manufactured by additive manufacturing. The holding method includes a heating of the holding assembly and the part blank to deform the first holding portion by fluid expansion in the inner cavity and to reduce a gap between the part blank and the holding assembly by expansion of the first holding portion in relation to the part blank.

Abstract: A method for manufacturing a part by additive manufacturing, the part to be manufactured including at least one portion to be held forming an angle of less than 45° with respect to a building direction of the part to be manufactured, the portion to be held having a first lateral surface and a second lateral surface opposite each other, the method comprising the steps of: providing a digital model of the part to be manufactured, adding to the digital model at least one holding element positioned on one side of the portion to be held, so as to be in contact with said first lateral surface or said second lateral surface.

Abstract: A dynamic seal for a turbomachine, including a fixed portion provided with at least one abradable wear part and a movable portion including at least one lip arranged to interact with the at least one wear part during the rotation of the movable portion. The wear part includes a structure forming cavities arranged in one or more series such that, in each series, the cavities of this series are superposed radially with respect to the central axis, the structure being configured to limit or prevent the circulation of gas between each pair of radially adjacent cavities. A method for the additive manufacture of the fixed portion of this dynamic seal is also described.

Abstract: An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

Abstract: The invention relates to a guide vane for a bypass aircraft turbomachine, its aerodynamic part comprising a first lubricant cooling interior passage in which heat transfer structures are arranged and a second lubricant cooling interior passage in which heat transfer structures are arranged, the aerodynamic part comprising a bent area connecting a lubricant output end of the first interior passage to a lubricant input end of the second passage, the bent area extending along a curved generatrix and being partly delimited by the intrados wall and the extrados wall of the vane. According to the invention, the bent area comprises one or more lubricant guide(s) arranged between the intrados and extrados walls of the vane, and each extending substantially parallel to the curved generatrix of the bent area.

Abstract: A method for manufacturing a part by additive manufacturing, the part to be manufactured including at least one portion to be held forming an angle of less than 45° with respect to a building direction of the part to be manufactured, the portion to be held having a first lateral surface and a second lateral surface opposite each other, the method comprising the steps of: providing a digital model of the part to be manufactured, adding to the digital model at least one holding element positioned on one side of the portion to be held, so as to be in contact with said first lateral surface or said second lateral surface.

Abstract: An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

Abstract: A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.

Abstract: The invention relates to a guide vane for a bypass aircraft turbomachine, its aerodynamic part comprising a first lubricant cooling interior passage in which heat transfer structures are arranged and a second lubricant cooling interior passage in which heat transfer structures are arranged, the aerodynamic part comprising a bent area connecting a lubricant output end of the first interior passage to a lubricant input end of the second passage, the bent area extending along a curved generatrix and being partly delimited by the intrados wall and the extrados wall of the vane. According to the invention, the bent area comprises one or more lubricant guide(s) arranged between the intrados and extrados walls of the vane, and each extending substantially parallel to the curved generatrix of the bent area.

Abstract: The invention relates to a guide vane for a twin-spool aircraft turbomachine, of which the aerodynamic part (32) comprises an internal lubricant cooling passage (50a) extending along a principal lubricant flow direction (52a). According to the invention, the aerodynamic part is made in a single piece and also comprises heat transfer fins (80a, 80b) arranged in the passage (50a) connecting the intrados and extrados walls (70, 72) and extending approximately parallel to the direction (52a), these fins being distributed in successive rows along the principal direction (52a) and made such that for two rows (R1, R2) of staggered directly consecutive fins, the row (R1) comprises fins (80a) forming a positive acute angle A1 with a dummy reference plane (Pf), while the row (R2) comprises fins (80b) forming a negative acute angle A2 with this plane (Pf).