The application discloses a high-B low-P nickel-based alloy and a preparation method therefor, belonging to the technical field of high-temperature alloys. The solution solves the problem that in the prior art, a nickel-based high-temperature alloy is difficult to meet comprehensive requirements of a component to have long alloy service life and low crack propagation rate at the same time. The high-B low-P nickel-based alloy comprises the following components in percentage by mass: C: 0.02% to 0.06%, Cr: 18.5% to 20.0%, Co: 13.0% to 14.0%, Mo: 4.0% to 4.90%, Al: 1.3% to 1.6%, Ti: 2.80% to 3.25%, B: 0.015% to 0.03%, Zr: 0.05% to 0.15%, Ti/Al: 2.25% to 2.38%, (Al + Ti): 4.35% to 4.58%, Fe: 0.05% to 2.0%, Mg ≤ 0.005%, P: 0.004% to 0.009%, O ≤ 20 PPm, N: ≤ 20 PPm, S ≤ 10 PPm, nickel: the remainder. The high-B low-P nickel-based alloy has high strength, good low-cycle fatigue performance, low crack propagation rate and excellent comprehensive performance.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
2.
NICKEL-BASED SUPERALLOY AND PREPARATION METHOD THEREFOR, AND STRUCTURAL COMPONENT
The present disclosure relates to the technical field of nickel-based superalloys, and in particular to a nickel-based superalloy and preparation method therefor, and a structural component. The alloy includes the following components in mass percentage: Co 17%-22%, Cr 9%-13%, Ta 2.95%-3.95%, Al 2.5%-3.5%, Ti 2.5%-3.5%, W 2.1%-3.5%, Mo 2.1%-3.5%, Nb 1.65%-1.95%, Hf 0.2%-0.7%, C 0.03%-0.08%, B 0.01%-0.06%, Zr 0.03%-0.07% and Ni. The nickel-based superalloys of the present disclosure, in the creep process at 780° C., produces specific Suzuki atmosphere in certain positions, and locks dislocations to improve creep resistance, such that the operating temperature can be raised to more than 780° C., which meets the requirements on the materials for the advanced aero-engines.
B22F 3/20 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittageAppareils spécialement adaptés à cet effet par extrusion
B22F 9/08 - Fabrication des poudres métalliques ou de leurs suspensionsAppareils ou dispositifs spécialement adaptés à cet effet par des procédés physiques à partir d'un matériau liquide par coulée, p. ex. à travers de petits orifices ou dans l'eau, par atomisation ou pulvérisation
C22C 1/02 - Fabrication des alliages non ferreux par fusion
3.
LOW-COST, HIGH-HOMOGENEITY AND LARGE-SPECIFICATION POWDER HIGH-TEMPERATURE ALLOY BAR, AND HOT EXTRUSION METHOD THEREFOR
The present application relates to a low-cost, high-homogeneity and large-specification powder high-temperature alloy bar, and a hot extrusion method therefor, belongs to the technical field of high-temperature alloy bars, and solves the problems of a small diameter, an uneven structure, a low material utilization rate, etc. of existing powder high-temperature alloy bars. The hot extrusion method comprises: injecting a high-temperature alloy powder into a vacuum stainless steel shell sheath to perform hot isostatic pressing, so as to obtain a powder high-temperature alloy ingot blank; respectively welding a front pad and a rear pad to the front end and the rear end of the powder high-temperature alloy ingot blank to obtain a first extrusion blank; preheating the first extrusion blank to 150-200ºC, uniformly coating the surface thereof with an anti-oxidation coating, heating same to 1040-1150ºC, and maintaining the temperature thereof, so as to obtain a second extrusion blank; uniformly spraying a lubricant onto the surface of the second extrusion blank, placing a glass pad at the front end thereof, and placing the second extrusion blank into a preheated extrusion die to perform extrusion, so as to obtain an extruded bar; and subjecting the extruded bar to air cooling to room temperature, and mechanically cutting off an unsteady-state section of the head and the tail to obtain a powder high-temperature alloy bar.
B22F 3/20 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittageAppareils spécialement adaptés à cet effet par extrusion
Disclosed in the present application are a disk-shaft integrated turbine disk and a preparation method therefor. The present application belongs to the technical field of turbine disks and solves the problem of it being difficult to meet the comprehensive requirements of high-temperature durability and low-cycle fatigue performance at the same time, which is caused by mixed crystals that are present in a disk-shaft integrated turbine disk in the prior art. The disk-shaft integrated turbine disk comprises a disk part and a shaft part which penetrates the disk part, wherein the disk part and the shaft part are integrally formed. The disk-shaft integrated turbine disk comprises the following components in percentages by mass: C: 0.02-0.04%, Cr: 18.5-20.0%, Co: 13.0-14.0%, Mo: 4.0-4.90%, Al: 1.3-1.6%, Ti: 2.80-3.25%, Ti/Al: 2.25-2.38, (Al+Ti): 4.35-4.58%, O: ≤20 ppm, N: ≤20 ppm, S≤10 ppm, P≤80 ppm and the balance of nickel. The disk-shaft integrated turbine disk of the present application has good comprehensive performance.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
F01D 5/02 - Organes de support des aubes, p. ex. rotors
C22C 1/02 - Fabrication des alliages non ferreux par fusion
5.
NICKEL-BASED SUPERALLOY AND PREPARATION METHOD THEREFOR, AND STRUCTURAL MEMBER
A nickel-based superalloy and a preparation method therefor, and a structural member. The alloy comprises the following components in percentages by mass: 17-22% of Co, 9-13% of Cr, 2.95-3.95% of Ta, 2.5-3.5% of Al, 2.5-3.5% of Ti, 2.1-3.5% of W, 2.1-3.5% of Mo, 1.65-1.95% of Nb, 0.2-0.7% of Hf, 0.03-0.08% of C, 0.01-0.06% of B, 0.03-0.07% of Zr, and Ni. During the creep process of the nickel-based superalloy at 780ºC, a specific Suzuki atmosphere is generated at a certain position to pin dislocation so as to improve the creep resistance, and the use temperature can be increased to 780ºC or more, such that the requirements of advanced aero-engines for materials can be met.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22C 1/04 - Fabrication des alliages non ferreux par métallurgie des poudres
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
F01D 5/02 - Organes de support des aubes, p. ex. rotors
6.
POWDER SUPERALLOY AND PREPARATION METHOD THEREFOR AND USE THEREOF
A powder superalloy and a preparation method therefor and the use thereof. The components of the powder superalloy comprise, in terms of mass fraction: Co, Cr, Mo, Nb, Al, Ta, Ti, C, Zr, Hf, W, B and Ni; the total mass fraction of Al, Ti, Nb and Ta in the powder superalloy is: (Al+Ti+Nb+Ta) is greater than 12 and less than 13.5; the mass ratio of Al to Ti is 1.0-1.2; the γ' phase content of the powder superalloy is 45%-55%; and the powder superalloy has excellent tensile properties and stress rupture properties at high temperature, and therefore can be used for manufacturing aero-engine turbine disks used at 750-830℃.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22C 1/04 - Fabrication des alliages non ferreux par métallurgie des poudres
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
7.
HIGH-CREEP-RESISTANCE NICKEL-BASED POWDER METALLURGY SUPERALLOY AND PREPARATION METHOD THEREFOR
A high-creep-resistance nickel-based powder metallurgy superalloy and a preparation method therefor, which belong to the technical field of superalloys, and are used for solving the problem of an existing nickel-based powder metallurgy superalloy having relatively low creep resistance at 815ºC. The superalloy comprises the following elements in mass fractions: 0.055-0.065% of C, 14.0-18.0% of Co, 9.0-11.0% of Cr, 2.3-2.7% of Mo, 4.0-6.0% of W, 4.0-6.0% of Ta, 3.0-3.4% of Al, 2.8-3.2% of Ti, 1.8-2.1% of Nb, 0.2-0.4% of Hf, 0.02-0.04% of Zr, 0.02-0.04% of B, 0.002-0.010% of Mg, 0.002-0.012% of La, and 0.002-0.012% of Ce, with the balance being Ni. The high-creep-resistance nickel-based powder metallurgy superalloy has high creep resistance at 815ºC or more.
A superalloy with low stacking fault energy includes by mass fraction 0.01%˜0.09% of C, 23.5%˜27.5% of Co, 11%˜15% of Cr, 0.1%˜1.8% of W, 2.2%˜2.6% of Al, 3.5%˜5.5% of Ti, 0%˜2% of Nb, 0%˜2% of Ta, 2.1%˜3.5% of Mo, 0.0001%˜0.05% of B, 0.0001%˜0.05% of Zr, 0%˜2.5% of Fe, 0%˜0.04% of Mg, 0%˜0.02% of Hf, and a balance of Ni, wherein a sum of the mass fractions of Nb and Ta is ≥0.8%. The superalloy is capable of service performance above 750° C. and good thermal processing characteristics, and is usable for structural members for long-term use, for example a turbine disc, a blade, a casing, a combustion chamber, etc. The superalloy has a structural member and an application thereof.
Provided are a nickel-based superalloy and a manufacturing method therefor, and a component and an application. The nickel-based superalloy is prepared from the following raw materials by means of 3D printing. The raw materials include (mass percent): less than or equal to 0.3% of C, less than 5% of Co, 13-15% of W, 20-24% of Cr, 1-3% of Mo, 0.2-0.5% of Al, less than 0.1% of Ti, less than 3% of Fe, less than 0.015% of B, 0.001-0.004% of La, 0.01-0.2% of Mn, and 0.02-0.2% of Si, with the balance being Ni. Average carbide size in a tissue is 150-200 nm, and carbide size distribution is 50 nm to 4 μm.
The present application relates to the field of superalloy, disclosing a method for internal stress regulation in superalloy disk forgings by pre-spinning. The method includes: Step S1, determining a target revolution for regulating internal stress in the disk forgings, and determining a target deformation magnitude of plastic deformation required for regulating the internal stress by the pre-spinning of the disk forgings; and Step S2, performing the pre-spinning of the disk forgings by the target revolution, monitoring a deformation magnitude of the disk forgings, and stopping the pre-spinning when a monitored deformation magnitude of the disk forgings reaches the target deformation magnitude.
C21D 8/02 - Modification des propriétés physiques par déformation en combinaison avec, ou suivie par, un traitement thermique pendant la fabrication de produits plats ou de bandes
C21D 9/40 - Traitement thermique, p. ex. recuit, durcissement, trempe ou revenu, adapté à des objets particuliersFours à cet effet pour anneauxTraitement thermique, p. ex. recuit, durcissement, trempe ou revenu, adapté à des objets particuliersFours à cet effet pour roulements de paliers
C21D 11/00 - Commande ou régulation du processus lors de traitements thermiques
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
11.
HIGH-TEMPERATURE ALLOY HAVING LOW STACKING FAULT ENERGY, STRUCTURAL MEMBER AND APPLICATION THEREOF
The present application relates to the technical field of high-temperature alloys, and in particular to a high-temperature alloy having low stacking fault energy, a structural member and an application thereof. The high-temperature alloy comprises, by mass fraction: C: 0.01%-0.09%, Co: 23.5%-27.5%, Cr: 11%-15%, W: 0.1%-1.8%, Al: 2.2%-2.6%, Ti: 3.5%-5.5%, Nb: 0%-2%, Ta: 0%-2%, Mo: 2.1%-3.5%, B: 0.0001%-0.05%, Zr: 0.0001%-0.05%, Fe: 0%-2.5%, Mg: 0%-0.04%, Hf: 0%-0.02%, and the remainder being Ni. The sum of the mass fractions of Nb and Ta is greater than or equal to 0.8%. The high-temperature alloy of the present application has service performance of more than 750°C and good hot-working characteristics, and can be used as a structural member such as a turbine disc, a blade, a casing and a combustion chamber for a long time.
The invention provides a preparation method of a nickel-based wrought superalloy wheel disk forging used at high temperature, in which the alloy has high content of solution strengthening elements W, Mo and strengthening phase γ′ phase forming elements Al, Ti, Nb and γ′ phase content reaches 55-65%. In view of a series of technical problems caused by high γ′ phase to alloy smelting and forging, the high-temperature stress relief annealing, low-temperature stress relief annealing process of steel ingot and high temperature homogenizing annealing of steel bar were proposed by optimizing the thermal process of wheel disk forging and controlling the precipitation and dissolution of γ′ phase.
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
The present disclosure relates to the technical field of alloys, and provides a nickel-based superalloy and a manufacturing method therefor, and a component and an application. The nickel-based superalloy is prepared from the following raw materials by means of 3D printing. The raw materials comprise (mass percent): less than or equal to 0.3% of C, less than 5% of Co, 13-15% of W, 20-24% of Cr, 1-3% of Mo, 0.2-0.5% of Al, less than 0.1% of Ti, less than 3% of Fe, less than 0.015% of B, 0.001-0.004% of La, 0.01-0.2% of Mn, and 0.02-0.2% of Si, with the balance being Ni. Average carbide size in a tissue is 150-200 nm, and carbide size distribution is 50 nm to 4 μm. The alloy has no cracks on the surface and inside, has high strength at high temperature and still has excellent performance at a temperature of 1100°C, and can thus meet the use requirements of aviation and aerospace.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22C 1/04 - Fabrication des alliages non ferreux par métallurgie des poudres
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p. ex. par frittage ou fusion laser sélectif
14.
METHOD FOR INTERNAL STRESS REGULATION IN SUPERALLOY DISK FORGINGS BY PRE-SPINNING
The present application relates to the field of superalloy, disclosing a method for internal stress regulation in superalloy disk forgings by pre-spinning. The method includes: Step Sl, determining a target revolution for regulating internal stress in the disk forgings, and determining a target deformation magnitude of plastic deformation required for regulating the internal stress by the pre-spinning of the disk forgings; and Step S2, performing the pre-spinning of the disk forgings by the target revolution, monitoring a deformation magnitude of the disk forgings, and stopping the pre-spinning when a monitored deformation magnitude of the disk forgings reaches the target deformation magnitude.
B21J 1/02 - Traitement préliminaire des matériaux métalliques sans mise en forme particulière, p. ex. conservation des propriétés physiques de certaines zones, forgeage ou pressage des pièces à l'état brut
15.
NICKEL-BASED DEFORMED HIGH-TEMPERATURE ALLOY HAVING HIGH ALUMINUM CONTENT AND PREPARATION METHOD THEREFOR
Provided is a nickel-based deformed high-temperature alloy having a high aluminum content and a preparation method therefor. Conventional Ni-Co-Cr components as matrix elements, the contents of alloy elements, especially the Al content of a solid solution strengthening phase γ' phase forming element, are increased, and the content of a strengthening phase γ' phase is increased to 55%-65%, so as to effectively improve the temperature bearing capability of the alloy. The appropriate addition of element Nb to the alloy can improve the stability of the γ' phase, thereby improving the performance of a casting-forging process, the reduction of the addition of element Cr can improve the long-term structural stability of the alloy at 850°C, and a high content of element Al can make up for the loss of surface stability caused by the decrease of element Cr. In addition, a dual process or triple process is used for the preparation and processing of an alloy raw material. The obtained nickel-based deformed high-temperature alloy solves the problem that there is no high-performance wheel forging material that can be used for a long time at 850℃, especially has excellent 850℃ tensile strength, yield strength and endurance life.
Disclosed is a method for preparing a nickel-based deformed high-temperature alloy turbine disk forging for high temperature use. The alloy has high contents of solution strengthening elements W and Mo and strengthening phase, i.e. γ' phase, formation elements Al, Ti and Nb. The content of the γ' phase reaches 55-65%. With regard to a series of technical difficulties brought about by the high level of the γ' phase in terms of the melting and forging of the alloy, by optimizing the thermal history of the process of preparing the turbine disk forging and by controlling the separation and dissolution of the γ' phase, a high-temperature stress-relief annealing and low-temperature stress-relief annealing process for a steel ingot and the high-temperature homogenizing annealing of a bar are proposed, thereby solving the problems of metallurgical defects being easily formed during the smelting of a nickel-based deformed high-temperature alloy turbine disk forging with a diameter of 100-1200 mm for use at a high temperature of 850°C, cracking easily occurring during forging, and the structure not being uniform.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22C 30/00 - Alliages contenant moins de 50% en poids de chaque constituant
C22C 1/02 - Fabrication des alliages non ferreux par fusion
C22C 1/06 - Fabrication des alliages non ferreux avec utilisation d'agents spéciaux d'affinage ou de désoxygénation
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
C22B 9/18 - Refusion sous laitier électroconducteur
Disclosed in this application are a large-sized high-Nb superalloy ingot and a smelting process thereof. The smelting process includes: vacuum induction melting to prepare a plurality of vacuum induction melting ingots with the same composition which are used for preparing electroslag electrodes with the same number as the vacuum induction melting ingots for use in electroslag remelting, preparing a consumable electrode from the prepared consumable electroslag electrodes, and performing vacuum consumable arc remelting for a plurality of times by using the consumable electroslag electrodes as raw material. A large-sized high-Nb superalloy ingot having a weight of 15 tons or above and a diameter of 800 mm or above can be prepared from such process.
Disclosed are a smelting process for a high-niobium high-temperature alloy large-size cast ingot, and a high-niobium high-temperature alloy large-size cast ingot. The smelting process comprises: carrying out vacuum induction smelting to prepare a plurality of vacuum induction ingots with the same components, further preparing the same number of electroslag electrodes, carrying out exchange electroslag remelting, then preparing consumable electrodes by using obtained electroslag ingots, and then carrying out vacuum consumable remelting multiple times by taking the consumable electrodes as initial raw materials. By means of the process, a high-niobium high-temperature alloy large-size cast ingot with an ingot weight of 15 tons or above and a diameter of 800 mm or more can be prepared, black spot and white spot metallurgical defect formation is inhibited to the maximum extent, the element segregation degree is reduced, and steel ingot bursting is effectively prevented.
22322) quaternary slag to exchange electroslag remelting, using the obtained electroslag ingot to obtain consumable electrode, then using the consumable electrode as the starting material to perform two vacuum consumable remelting. This process can be used to prepare large-size ingots of high-niobium and high-temperature 706 alloy with an ingot weight of more than 15 tons and a diameter of more than 800 mm, minimizing the formation of black spots and white spots metallurgical defects, and reducing the burning rate of Al and Ti elements.
brevets
