Abstract: The invention relates to a de-icing splitter nose (22) of an axial turbine engine, notably a de-icing splitter nose of a turbo-jet engine compressor. The splitter nose includes an annular row of vanes (26), each of which has a radially extending leading edge (36), and a de-icing system (28) based on hot-air injection. The injection is pulsed, i.e. discontinuous. The system (28) includes an annular row of injection orifices for injecting de-icing fluid (44) onto the vanes (26) in respective injection directions (46). Each injection orifice is associated with a vane such that the injection directions thereof are substantially parallel to the leading edge (36) of the related vane, enabling said vane (26) to be de-iced.

Abstract: A composition for an abradable seal for a turbomachine, in particular in powder form, is able to crumble in the event of contact with a rotor of said turbomachine. The seal is formed on the arcuate wall of a substrate casing. The composition includes a majority metallic phase with a majority by mass of aluminium with some chromium, a minority second phase including a mineral material and/or an organic material.

Abstract: The present invention relates to a three-dimensional printer in which a localized powder flow is deposited on a construction surface. The three-dimensional printer comprises an electrostatic charge detector for measuring a characteristic of an electrostatic charge of the powder flow, for example the electrostatic charge thereof or the electrostatic charge thereof per unit of time. Said detector makes it possible to prevent explosions caused by the accumulation of electrostatic charge.

Abstract: The invention relates to a composition for an abradable seal of a turbomachine, the composition comprising an aluminum base, nickel powder, polyester powder. The invention also relates to an outer casing of a low-pressure compressor of an axial-flow turbomachine with an abradable seal surrounding an annular row of rotor blades. The seal comprises a rounded support covered with a layer of abradable material comprising a metallic phase mainly made of aluminum and with nickel in a lesser proportion. The abradable material additionally comprises from 25% to 55% of additive, such as polyester, methyl methacrylate, hexagonal boron nitride, calcium fluoride. The support is segmented, and forms an organic matrix composite outer casing of the compressor. The invention also proposes a process for producing an abradable seal by plasma spraying an Al—Ni-polyester powder.

Abstract: The invention relates to a de-icing splitter nose (22) of an axial turbine engine, notably a de-icing splitter nose of a turbo-jet engine compressor. The splitter nose includes an annular row of vanes (26), each of which has a radially extending leading edge (36), and a de-icing system (28) based on hot-air injection. The injection is pulsed, i.e. discontinuous. The system (28) includes an annular row of injection orifices for injecting de-icing fluid (44) onto the vanes (26) in respective injection directions (46). Each injection orifice is associated with a vane such that the injection directions thereof are substantially parallel to the leading edge (36) of the related vane, enabling said vane (26) to be de-iced.

Abstract: The invention relates to a composition for an abradable seal of a turbomachine, the composition comprising an aluminium base, nickel powder, polyester powder. The invention also relates to an outer casing of a low-pressure compressor of an axial-flow turbomachine with an abradable seal surrounding an annular row of rotor blades. The seal comprises a rounded support covered with a layer of abradable material comprising a metallic phase mainly made of aluminium and with nickel in a lesser proportion. The abradable material additionally comprises from 25% to 55% of additive, such as polyester, methyl methacrylate, hexagonal boron nitride, calcium fluoride. The support is segmented, and forms an organic matrix composite outer casing of the compressor. The invention also proposes a process for producing an abradable seal by plasma spraying an Al—Ni-polyester powder.

Abstract: A method for manufacturing a machine structural element from a molded composite material includes manufacturing of an abradable layer made integrally from the material of the element. The method consists in adding a filler material to the resin at the surface to be made abradable, the filler material being able to disintegrate, such as e.g. transitioning to vapor phase, during the heat treatment of polymerizing the resin in order to create porosity inside the layer. The porosity thus created provides the relevant surface with properties of abradability.

Abstract: A method for manufacturing a machine structural element from a molded composite material includes manufacturing of an abradable layer made integrally from the material of the element. The method consists in adding a filler material to the resin at the surface to be made abradable, the filler material being able to disintegrate, such as e.g. transitioning to vapor phase, during the heat treatment of polymerizing the resin in order to create porosity inside the layer. The porosity thus created provides the relevant surface with properties of abradability.