Abstract: The invention concerns a method for manufacturing an aircraft part, the part comprising a monocrystalline nickel-based superalloy substrate, the method consecutively implementing the steps of moulding the part at a moulding temperature greater than the melting temperature of the superalloy, and cooling the part, such that the monocrystalline superalloy has a ? phase and a ? phase, solution heat treatment of the part at a first temperature between the solves temperature of the ?? phase and the melting temperature of the superalloy, homogenising the crystalline structure or the part, cooling the part to ambient temperature, first tempering and second tempering.

Abstract: The invention relates to a nickel-based superalloy comprising in weight percentages: 5.0 to 6.0% of aluminium, 6.0 to 9.0% of tantalum, 1.0 to 5.0% of cobalt, 5.0 to 7.5% of chromium, 0 to 1.0% of molybdenum, 4.0 to 6.0% of tungsten, 0.50 to 3.5% of rhenium, 1.0 to 4.0% of platinum, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and to a turbomachine comprising such a blade.

Abstract: The invention concerns a method for manufacturing an aircraft part, the part comprising a monocrystalline nickel-based superalloy substrate, the method consecutively implementing the steps of moulding the part at a moulding temperature greater than the melting temperature of the superalloy, and cooling the part, such that the monocrystalline superalloy has a ? phase and a ? phase, solution heat treatment of the part at a first temperature between the solves temperature of the ?? phase and the melting temperature of the superalloy, homogenising the crystalline structure or the part, cooling the part to ambient temperature, first tempering and second tempering.

Abstract: The invention relates to a nickel-based superalloy comprising, in percentages by mass, 5.0 to 6.0% aluminum, 6.0 to 9.5% tantalum, 0 to 1.50% titanium, 8.0 to 10.0% cobalt, 6.0 to 7.0% chromium, 0.30 to 0.90% molybdenum, 5.5 to 6.5% tungsten, 0 to 2.50% rhenium, 0.05 to 0.15% hafnium, 0.70 to 4.30% platinum, 0 to 0.15% silicon, the remainder being nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and a turbomachine comprising such a blade.

Abstract: A superalloy component heat treatment method using controlled induction heat treatment. The method being adapted to controllably generate a coarse grain microstructure region within the component from a fine grain microstructure metallic component. The method further being adapted to controllably form precipitates within the desired region in order to achieve a desired hardness therein. A single piece alloy component having a controlled core region and a controlled peripheral region. The controlled core region defining fine metallurgical grains and adapted to provide a desired fatigue resistance. The controlled peripheral region defining coarse metallurgical grains and adapted to provide a desired creep resistance.

Abstract: The invention relates to a nickel-based superalloy comprising, in percentages by mass, 5.0 to 6.0% aluminum, 6.0 to 9.5% tantalum, 0 to 1.50% titanium, 8.0 to 10.0% cobalt, 6.0 to 7.0% chromium, 0.30 to 0.90% molybdenum, 5.5 to 6.5% tungsten, 0 to 2.50% rhenium, 0.05 to 0.15% hafnium, 0.70 to 4.30% platinum, 0 to 0.15% silicon, the remainder being nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and a turbomachine comprising such a blade.

Abstract: A turbine component such as a turbine blade or a vane of a distributor, which includes a polycrystalline substrate containing grains, the substrate having at least one Ti3AlC2 phase and the mass fraction of the phase of the alloy is greater than 97%, with the average length of the grains is less than 50 ?m, the average width-to-length ratio is between 0.4 and 0.6, and the average mesh volume of the Ti3AlC2 phase is less than 152.4 ?3.

Abstract: A superalloy component heat treatment method using controlled induction heat treatment. The method being adapted to controllably generate a coarse grain microstructure region within the component from a fine grain microstructure metallic component. The method further being adapted to controllably form precipitates within the desired region in order to achieve a desired hardness therein. A single piece alloy component having a controlled core region and a controlled peripheral region. The controlled core region defining fine metallurgical grains and adapted to provide a desired fatigue resistance. The controlled peripheral region defining coarse metallurgical grains and adapted to provide a desired creep resistance.