Ceramic core used for the production of a hollow turbine blade of a turbomachine by the lost wax casting method and shaped to constitute the cavities of said blade in a single component comprising in order to jointly supply the interior of said cavities with cooling air core portions (60 62) intended to form the fir...

The invention proposes a system (10) for suspending a mobile mass (12) such as an inertial angular rate sensor comprising a linking device (32A) comprising first and second linking elements (34A 36A) linked to one another by a linking unit (38A) and deformable by bending in a mobility plane (P) so as to allow respec...

The invention concerns a turbine component such as a turbine blade or a distributor fin for example comprising a substrate made from single-crystal nickel superalloy and a metal sublayer covering the substrate characterised in that the metal sublayer comprises at least two elementary layers including a first element...

The invention relates to a superalloy based on nickel, comprising, in mass percentages, 4.0 to 6.0 % of chromium, 0.4 to 0.8 % of molybdenum, 2.5 to 3.5 % of rhenium, 6.2 to 6.6 % of tungsten, 5.2 to 5.7 % of aluminium, 0.0 to 1.6 % of titanium, 6.0 to 9.9 % of tantalum, 0.0 to 0.7 % of hafnium, and 0.0 to 0.3 % of ...

The invention relates to a turbine part, such as a turbine blade or a distributor fin, for example, comprising a substrate made of superalloy based on monocrystalline nickel, comprising rhenium and/or ruthenium, and having a γ'-NisAI phase that is predominant by volume and a γ-Ni phase, the part also comprising a su...

The invention relates to an aviation turbine blade (10) characterised in that it comprises at least a first lower surface cavity (C2) and a first upper surface cavity (C3) each adjacent to a first through-cavity (C1) and a second through-cavity (C4) the first upper surface cavity (C3) being adjacent to the upper sur...

The invention relates to a turbine blade comprising a blade root and a blade (13) extending radially outwards from the blade root (12) said blade (13) comprising a first inner cooling circuit comprising a lower surface cavity (33 36) extending radially along the lower surface wall (16) and along a first inner wall (...

The invention relates to a turbine component comprising a substrate made from monocrystalline nickel-based superalloy comprising rhenium, which has a ?-?' Ni phase, and an average weight fraction of chromium of less than 0.08, a sublayer made from nickel-based metal superalloy covering the substrate, characterized i...

The invention relates to a part made from a composite material having a ceramic matrix and comprising a protection device, the protection comprising a coating layer having a gradual composition. The aforementioned gradual-composition coating layer comprises at least one silicon phase and one aluminium phase, the pro...

The invention concerns a component (10) comprising: a substrate (20) of which at least one part adjacent to a surface (S) of the substrate is made from a material comprising silicon; a bonding sublayer (30) situated on the surface (S) of the substrate and comprising silicon, an environmental barrier (40) that compri...

The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer ...

The present invention relates to a core for metal casting an aeronautical part such as a turbine blade, the core being designed for arrangement in an inner cavity defined by a mould, the core comprising: a body (13) intended to form the inner shape of the turbine blade; and an impact portion (15), disposed along at ...

The invention relates to a nickel-based superalloy comprising, in weight percentages, 5.9 to 6.5% of aluminum, 9.5 to 10.5% of cobalt, 4 to 5% of chromium, 0.1 to 0.2% of hafnium, 0.3 to 0.7% of molybdenum, 3.7 to 4.5% of rhenium, 7.5 to 8.5% of tantalum, 0.2 to 0.7% of titanium, 3.2 to 4% of tungsten, 0 to 0.1% of ...

The invention relates to a nickel-based superalloy comprising, in weight percentages, 6 to 8% of aluminum, 12 to 15% of cobalt, 4 to 8% of chromium, 0 to 0.2% of hafnium, 0.5 to 4% of molybdenum, 3.5 to 6% of rhenium, 4 to 6% of tantalum, 1 to 3% of titanium, 0 to 2% of tungsten, 0 to 0.1% of silicon, the remainder ...

The invention relates to new superalloy compositions having a limited density and having, in the hot state, good mechanical properties as well as good resistance to oxidation and corrosion.

The invention relates to a sensor-type or actuator-type MEMS or NEMS device provided with a stacked stop element comprising - a first flat layer having a first flat electrode intended to be at a first electric potential and a second flat electrode intended to be at a second electric potential different from the firs...

The invention relates to a resonator (1) that is configured to be integrated into an inertial angle sensor said resonator (1) comprising at least one mass suspended by mechanical springs (5) and a number N of pairs Pi (2 = i = N) of electrostatic springs (50) said resonator (1) defining at least four axes of symmetr...

The invention relates principally to a cluster model and a shell (1) for the production by lost wax casting of a plurality of turbomachine elements the shell (1) comprising a central sprue (3) that is fluidically connected to a casting cup (2) for receiving the molten metal and a plurality of shell elements (4). The...

The invention relates to a method for monitoring the soundness of helicopters comprising the determination of the severity of a plurality of flight missions of a plurality of helicopters comprising a step for acquiring and storing flight data from helicopter flight missions and a step for acquiring and storing maint...

Aeronautical turbine blade (10) comprising pressure-face-side cavities and suction-face-side cavities extending radially, and at least one central cavity situated in the central part of the blade (10) and surrounded by pressure-face-side and suction-face-side cavities, the blade (10) also comprising cooling circuits...

A coated turbomachine part (20) comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (22) present on the substrate (21). The protective layer (22) comprises a first phase (220) of a material for protection against the calcium and magnesium aluminosilicates CMA...

A coated turbomachine part comprises a substrate (21) and a layer for protection against the calcium and magnesium aluminosilicates CMAS (24) present on the substrate (21). The layer (24) comprises a first phase (240) of a material for protection against the calcium and magnesium aluminosilicates CMAS and a second p...

The invention relates to a nickel-based superalloy comprising, in weight percentages, 4.0 to 5.5 % rhenium, 3.5 to 12.5 % cobalt, 0.30 to 1.50 % molybdenum, 3.5 to 5.5 % chromium, 3.5 to 5.5 % tungsten, 4.5 to 6.0 % aluminum, 0.35 to 1.50 % titanium, 8.0 to 10.5 % de tantalum, 0.15 to 0.30 % hafnium, 0.05 to 0.15 % ...

The invention relates to a nickel-based superalloy comprising, in weight percentages, 4.0 to 5.5 % rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0 % cobalt, 0.3 to 1.0 % molybdenum, 3.0 to 5.0 % chromium, 2.5 to 4.0 % tungsten, 4.5 to 6.5 % aluminium, 0.50 to 1.50 % titanium, 8.0 to 9.0 % de tantalum, 0.15 to 0.30 % hafn...

The invention relates to a propulsion system (100) for an aircraft, comprising at least one rotor (110) and a nacelle cowling (120) extending around the at least one rotor (110), said nacelle cowling (120) being sectored and comprising at least one sector (130a, 130b) which is fixed and sectors (141a, 141b, 142a, 14...

The invention relates to a nickel-based superalloy comprising, in weight percentages, 4 to 6% of aluminum, 5 to 8% of cobalt, 6 to 9% of chromium, 0.1 to 0.9% of hafnium, 2 to 4% of molybdenum, 5 to 7% of rhenium, 5 to 7% of tantalum, 2 to 5% of tungsten, 0 to 0.1% of silicon, the remainder being nickel and inevitab...

The invention relates to a method for producing a part made of a nickel-based alloy with a Y/Y' microstructure in which at least one hot-forging step is performed, which method is characterised in that the temperature at which the part is heated in the forging step is maintained within a temperature range lower than...