A kind of 850 ℃ deformed turbine disk alloy material and preparation process
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An alloy material and turbine disk technology is applied in the field of deformed superalloy materials for aero-engine turbine disks. The effect of segregation
Active Publication Date: 2022-04-19
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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One of them is an invention patent declared by the Metal Institute of the Chinese Academy of Sciences: a nickel-cobalt-based superalloy containing rare earth elements and its preparation method (CN201010296131.0), which is mainly aimed at aero-engine turbine disks and blades used under high stress at 700-750°C. The alloy composition (wt%) is: C<0.1, Co: 15-30, Cr: 11-17, Ti: 4-6.5, Al: 1.0-3.0, W: 0.5-2.5, Mo: 1-3, Re: 0~2, Zr<0.1, B<0.1, rare earth: 0.01-0.5, Ni: balance, and the invention adopts vacuum induction furnace or vacuum consumable furnace for smelting, from the alloy composition range to the smelting process, it is the same as the patent application There is a big difference; another invention patent is the smelting process of a new nickel-iron-based superalloy GH4169D proposed by Fushun Special Steel (CN201410741910.5). Although this process also uses triple smelting, it is aimed at a low degree of alloying , using the GH4169D alloy with a temperature of only 704°C, the alloy composition of this patent is quite different from that of the present invention
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Embodiment 1
[0046] Procurement of metal raw materials: Jinchuan No. 0 nickel, low-nitrogen chromium (purity ≥99.3%), electrolytic cobalt (purity ≥99%), high-purity iron (purity ≥99.6%), molybdenum (Mo), niobium (Nb), aluminum (Al ), titanium (Ti), silicon (Si), high-purity graphite carbon (purity > 99.9%), rare earth elements cerium (Ce), lanthanum (La), yttrium (Y), boron-iron, nickel-magnesium master alloy; ingredients. Dosing according to the design composition: C: 0.1%; Al: 4.5%; Ti: 2.0%; Nb: 1.0%; W: 9.5%; Mo: 1.0%; Co: 14.0%; Cr: 7.5%; B: 0.006% ; Mg: 0.005%; Ce: 0.001%; La: 0.001%; Y: 0.01%; Si: 0.01%; Put Ni, Co, Cr, W, Mo, Nb, Al, Ti, etc. into the crucible of the vacuum induction melting furnace, transmit electricity and melt, and the maximum temperature of vacuum induction melting is 1520°C. After the metal material is completely melted, add iron-boron, nickel-magnesium, silicon, and Ce, La, and Y elements for further refining; the refined high-temperature alloy melt is c...
Embodiment 2
[0048] Procurement of metal raw materials: Jinchuan No. 0 nickel, low-nitrogen chromium (purity ≥99.3%), electrolytic cobalt (purity ≥99%), high-purity iron (purity ≥99.6%), molybdenum (Mo), niobium (Nb), aluminum (Al ), titanium (Ti), silicon (Si), high-purity graphite carbon (purity > 99.9%), rare earth elements cerium (Ce), lanthanum (La), yttrium (Y), boron-iron, nickel-magnesium master alloy; ingredients. Dosing according to the design composition: C: 0.15%; Al: 5.2%; Ti: 3.0%; Nb: 2.0%; W: 11.0%; Mo: 1.5%; Co: 17.0%; Cr: 10.0%; B: 0.01% ; Mg: 0.01%; Ce: 0.02%; La: 0.02%; Y: 0.03%; Si: 0.3%; Put Ni, Co, Cr, W, Mo, Nb, Al, Ti, etc. into the crucible of the vacuum induction melting furnace, transfer electricity to melt, and the maximum temperature of vacuum induction melting is 1560°C. After the metal material is completely melted, add iron-boron, nickel-magnesium, silicon, and Ce, La, and Y elements for further refining; the refined high-temperature alloy melt is cast int...
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Abstract
The invention belongs to the field of deformed superalloy materials for aero-engine turbine discs; it relates to a deformed turbine disc alloy material for 850°C and a preparation process; the invention generates carbides in the alloy by adding higher element C, and through control The addition of W and Mo elements avoids the precipitation of TCP phase in the alloy; adding trace rare earth elements to the alloy for composite microalloying, further improving the thermal strength of the alloy, and using pre-melted slag containing rare earth elements for electroslag remelting. The electroslag used for remelting adds trace rare earth elements to ensure the alloy composition; the segregation of the ingot composition is small; the alloy of the present invention uses a small-sized electrode ingot, and at the same time, combined with the triple smelting process, it helps to reduce the alloy composition segregation. The alloy prepared by the invention has the advantages of uniform composition, good high-temperature mechanical properties and the like, and can meet the requirements of high-thrust ratio advanced aero-engines for high-performance deformed alloy turbine disk materials.
Description
technical field [0001] The invention belongs to the field of deformed high-temperature alloy materials for aero-engine turbine disks, and relates to a deformed turbine disk alloy material for 850°C and a preparation process. Background technique [0002] The background technology of this patent is the composition design technology and melting technology of deformed superalloys for aero-engine turbine disks. [0003] Deformed superalloys have excellent comprehensive mechanical properties and good corrosion resistance, and are one of the key materials for aerospace engines and gas turbine turbine disks. With the increase of the thrust-to-weight ratio of aero-engines, the temperature of the gas in front of the turbine continues to increase, and the requirements for the temperature-bearing capacity of the turbine disk alloy are also getting higher and higher. The temperature capacity index is the highest temperature that the alloy can withstand under the given external force an...
Claims
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