CN115418531B - Low-density nickel-based superalloy, and preparation method and application thereof - Google Patents
Low-density nickel-based superalloy, and preparation method and application thereof Download PDFInfo
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- CN115418531B CN115418531B CN202211144707.0A CN202211144707A CN115418531B CN 115418531 B CN115418531 B CN 115418531B CN 202211144707 A CN202211144707 A CN 202211144707A CN 115418531 B CN115418531 B CN 115418531B
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 75
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 50
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 37
- 238000002360 preparation method Methods 0.000 title abstract description 15
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 87
- 239000000956 alloy Substances 0.000 claims abstract description 87
- 239000012535 impurity Substances 0.000 claims abstract description 10
- 229910052720 vanadium Inorganic materials 0.000 claims description 14
- 238000007670 refining Methods 0.000 claims description 10
- 238000010438 heat treatment Methods 0.000 claims description 8
- 238000004519 manufacturing process Methods 0.000 claims description 6
- 238000005266 casting Methods 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 230000006698 induction Effects 0.000 claims description 4
- 238000002844 melting Methods 0.000 claims description 4
- 230000008018 melting Effects 0.000 claims description 4
- 239000002994 raw material Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 claims 1
- 238000003466 welding Methods 0.000 abstract description 16
- 238000005242 forging Methods 0.000 abstract description 11
- 230000015572 biosynthetic process Effects 0.000 abstract description 8
- 230000002045 lasting effect Effects 0.000 abstract description 4
- 230000000052 comparative effect Effects 0.000 description 34
- 239000000203 mixture Substances 0.000 description 25
- 230000000694 effects Effects 0.000 description 13
- 230000032683 aging Effects 0.000 description 7
- 230000007797 corrosion Effects 0.000 description 7
- 238000005260 corrosion Methods 0.000 description 7
- 238000005728 strengthening Methods 0.000 description 7
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 6
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 5
- 230000006378 damage Effects 0.000 description 5
- 229910000831 Steel Inorganic materials 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000003647 oxidation Effects 0.000 description 4
- 238000007254 oxidation reaction Methods 0.000 description 4
- 239000006104 solid solution Substances 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 238000005336 cracking Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 3
- 229910052742 iron Inorganic materials 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 238000004220 aggregation Methods 0.000 description 2
- 230000002776 aggregation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000001771 impaired effect Effects 0.000 description 2
- 238000009776 industrial production Methods 0.000 description 2
- 230000005923 long-lasting effect Effects 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 238000005204 segregation Methods 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 239000011651 chromium Substances 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000007872 degassing Methods 0.000 description 1
- 238000006477 desulfuration reaction Methods 0.000 description 1
- 230000023556 desulfurization Effects 0.000 description 1
- 230000003009 desulfurizing effect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/023—Alloys based on nickel
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of alloys, and particularly relates to a low-density nickel-based superalloy, a preparation method and application thereof. The low-density nickel-based superalloy provided by the invention comprises: c:0.04-0.08%, cr:18.00-20.50%, co:9.10-11.00%, mo:8.10-9.00%, al:1.38-1.65%, ti:1.9-2.3%, zr:0-0.02%, nd:0.07-0.15% and B:0.004-0.01%, and the balance of nickel and unavoidable impurities, based on mass percent. The alloy has lower density, excellent lasting life and high-temperature tensile property at 700 ℃, and no crack formation in welding and forging, thereby meeting the use requirement.
Description
Technical Field
The invention belongs to the technical field of alloys, and particularly relates to a low-density nickel-based superalloy, a preparation method and application thereof.
Background
The high-temperature alloy is a metal material which is based on iron, nickel and cobalt, can work for a long time under the action of a certain stress at the high temperature of above 600 ℃, and has the comprehensive properties of higher high-temperature strength, good oxidation resistance and corrosion resistance, good fatigue property, fracture toughness and the like. The superalloy has a single austenitic structure, and has good structural stability and use reliability at various temperatures. Then, a superalloy using nickel as a matrix (content of which is generally more than 50%) having high strength and excellent oxidation resistance and gas corrosion resistance in the range of 650 to 1000 ℃ is called a nickel-based superalloy (hereinafter referred to as "nickel-based alloy").
Nickel-based superalloys are the most widely used of the superalloys and have the highest strength at high temperatures. The main reason is that the nickel-based alloy can dissolve more alloy elements and can keep better tissue stability; secondly, can form A in coherent order 3 The B-type intermetallic compound effectively strengthens the alloy and obtains higher high-temperature strength than iron-based superalloy and cobalt-based superalloy; thirdly, the nickel-based alloy containing chromium has better oxidation resistance and gas corrosion resistance than the iron-based superalloy.
Disclosure of Invention
The present invention has been made based on the findings and knowledge of the inventors regarding the following facts and problems:
nickel-based superalloy refers to a superalloy with nickel as a matrix (content typically greater than 50%) having high strength and good oxidation and gas corrosion resistance in the range of 650-1000 ℃. Although the heat corrosion resistance of the existing nickel-based alloy is better, as the high temperature resistance requirement of each industry on the high temperature resistant alloy is higher and higher, the nickel-based high temperature alloy in the prior art cannot meet the use requirement, and the nickel-based high temperature alloy with higher temperature resistance needs to be prepared to meet the use requirement.
The present invention aims to solve at least one of the technical problems in the related art to some extent. Therefore, the embodiment of the invention provides a low-density nickel-based superalloy, which has lower density, excellent lasting life and high-temperature tensile property at 700 ℃, and has no crack formation in welding and forging, thereby meeting the use requirement.
The embodiment of the invention provides a low-density nickel-based superalloy, which comprises the following components: c:0.04-0.08%, cr:18.50-20.50%, co:9.10-11.00%, mo:8.10-9.00%, al:1.38-1.65%, ti:1.9-2.3%, zr 0-0.02%, nd:0.07-0.15% and B:0.004-0.01%, and the balance of nickel and unavoidable impurities, based on mass percent.
The low-density nickel-base superalloy of the embodiment of the invention has the advantages and technical effects that 1, in the embodiment of the invention, W element is not added, the solid solution strengthening effect of W in the nickel-base superalloy is obvious, but W is an element accelerating high-temperature corrosion, and harmful delta phase can be formed when the nickel-base superalloy is in long-term service, the alloy strength and toughness are reduced, in addition, the density of W is larger, and the density of W is 19.25g/cm 3 Considering that the alloy in the embodiment of the invention is mainly used on aeroengines and gas turbines, the lighter the required material is, the better, so W is not added in the alloy in the embodiment of the invention; 2. in the embodiment of the invention, nb is not added, nb is a forming element of a strengthening phase gamma ', the quantity of gamma ' is increased along with the increase of the Nb content, the high-temperature creep deformation and the durability are improved, but excessive gamma ' can deteriorate the welding performance and damage the processing performance, in addition, nb can be combined with C to form MC-type carbide, the grain boundary growth and the grain boundary sliding are prevented at high temperature, the effect of improving the high-temperature mechanical performance is achieved, but Nb can form large-particle MC-type carbide at the same time, the mechanical performance of the alloy is adverse, in addition, excessive Nb can damage the welding performance, the strain aging cracking sensitivity of the alloy is enhanced, the defect of welding cracks is easy to appear, and the effect of Nb is comprehensively considered, and the Nb is not added in the embodiment of the invention; 3. in the embodiment of the invention, nd element is added, nd has strong deoxidizing and desulfurizing capability, can purify molten steel, delay carbide precipitation and aggregation growth along a grain boundary, can also prevent the formation and expansion of grain boundary cracks, and can weaken or eliminate the segregation of impurity elements at the grain boundary, therebyThe strengthening of grain boundary plays a role in improving the high-temperature durable life and creep resistance of alloy, and Nd is characterized in that the high-temperature performance of alloy can be obviously improved with a small addition amount, the hot processing performance is damaged when the addition amount is too large, forging cracks are caused, and large-size inclusions are formed and are harmful to the performance of alloy. Therefore, the Nd content is controlled within the range of 0.07-0.15% in the embodiment of the invention; 4. in the embodiment of the invention, the alloy has excellent room temperature tensile property, long service life, lower density and no hot welding and forging crack formation by adopting the element composition of the design proportion, thereby meeting the design and use requirements of an advanced aeroengine and a gas turbine.
In some embodiments, the low density nickel-base superalloy further comprises 0.8-1.5 mass% V.
In some embodiments, the V is 0.86-1.43% by mass.
In some embodiments, the mass percent of Al, nd, and V satisfies the relationship 0.92% < al+2.8nd—0.6v <1.43%.
In some embodiments, the mass percent content of Al, nd, and V satisfies the relationship 0.94% < al+2.8nd—0.6v <1.39%.
In some embodiments, the low density nickel-base superalloy comprises: c:0.05-0.068%, cr:18.50-20.50%, co:9.15-9.8%, mo:8.10-9.00%, al:1.40-1.62%, ti:2.12-2.25%, zr:0-0.02%, nd:0.075-0.15% and B:0.004-0.009%, and the balance being nickel and unavoidable impurities, in mass percent.
The embodiment of the invention also provides application of the low-density nickel-based superalloy in an aeroengine.
The embodiment of the invention also provides application of the low-density nickel-base superalloy in a gas turbine.
The embodiment of the invention also provides a preparation method of the low-density nickel-based superalloy, which comprises the following steps:
(1) Adding the raw materials into a vacuum induction melting furnace according to the proportion, and heating to 1550-1650 ℃ for refining;
(2) Cooling to 1450-1550 ℃ for casting to form a high-temperature alloy cast ingot;
(3) And (3) carrying out heat treatment on the high-temperature alloy cast ingot obtained in the step (2) for 20-40 h at 800-1000 ℃.
The low-density nickel-base superalloy prepared by the preparation method has the advantages and technical effects that 1, in the embodiment of the invention, the low-density nickel-base superalloy prepared by the preparation method has excellent room-temperature tensile property, long service life, lower density, no hot welding and forging crack formation, and meets the design and use requirements of advanced aeroengines and gas turbines; 2. in the embodiment of the invention, the preparation method is simple, reduces the energy consumption, shortens the production period, improves the production efficiency, and is suitable for popularization and application in industrial production.
In some embodiments, in the step (1), the high temperature refining time is 20 to 40 minutes.
Detailed Description
The following detailed description of embodiments of the invention is exemplary and intended to be illustrative of the invention and not to be construed as limiting the invention.
The embodiment of the invention provides a low-density nickel-based superalloy, which comprises the following components: c:0.04-0.08%, cr:18.00-20.50%, co:9.10-11.00%, mo:8.10-9.00%, al:1.38-1.65%, ti:1.9-2.3%, zr:0-0.02%, nd:0.07-0.15% and B:0.004-0.01%, and the balance of nickel and unavoidable impurities, based on mass percent.
The low-density nickel-base superalloy of the embodiment of the invention has the advantages and technical effects that W element is not added, the solid solution strengthening effect of W in the nickel-base superalloy is obvious, but W is an element accelerating high-temperature corrosion, and harmful delta phase can be formed when the alloy is in long-term service, the alloy strength and toughness are reduced, in addition, the density of W is larger, and the density of W is 19.25g/cm 3 Considering that the alloy in the embodiment of the invention is mainly used on aeroengines and gas turbines, the lighter the required material is, the better, so W is not added in the alloy in the embodiment of the invention; in the embodiment of the invention, no additional components are addedNb is a forming element of a strengthening phase gamma ', and increases the quantity of gamma ' along with the increase of the Nb content, so that the high-temperature creep deformation and the durability are improved, but excessive gamma ' can deteriorate the welding performance and damage the processing performance, in addition, nb can be combined with C to form MC-type carbide, the grain boundary growth and the grain boundary sliding are prevented at high temperature, the effect of improving the high-temperature mechanical performance is achieved, but Nb can form large-particle MC-type carbide at the same time, the mechanical performance of the alloy is adverse, in addition, excessive Nb can damage the welding performance, so that the strain aging cracking sensitivity of the alloy is enhanced, the welding crack defect is easy to appear, and the effect of Nb is comprehensively considered, so that Nb is not added in the embodiment of the invention; in the embodiment of the invention, nd element is added, nd has strong deoxidization and desulfurization capability, can purify molten steel, delay carbide precipitation and aggregation growth along a grain boundary, can also prevent the formation and expansion of grain boundary cracks, and can weaken or eliminate the segregation of impurity elements at the grain boundary so as to strengthen the grain boundary, thereby playing the role of improving the high-temperature durable service life and creep resistance of alloy. Therefore, the embodiment of the invention controls the Nd content to be in the range of 0.07-0.15%. In the embodiment of the invention, the alloy has excellent room temperature tensile property, long service life, lower density and no hot welding and forging crack formation by adopting the element composition of the design proportion, thereby meeting the design and use requirements of an advanced aeroengine and a gas turbine.
In some embodiments, preferably, the low density nickel-base superalloy comprises: c:0.05-0.068%, cr:18.50-20.50%, co:9.15-9.8%, mo:8.10-9.00%, al:1.40-1.62%, ti:2.12-2.25%, zr:0-0.02%, nd:0.075-0.15% and B:0.004-0.009%, and the balance being nickel and unavoidable impurities, in mass percent.
In some embodiments, preferably, the low density nickel-base superalloy further comprises 0.8-1.5 mass% V. Further preferably, the mass percentage of V is 0.86-1.43%.
In the embodiment of the invention, the element V is added into the alloy, V is a strong carbide and gamma' forming element, and V can replace Ni 3 The position of Al in Al (gamma') improves the stability, V can be dissolved in the matrix, so that the lattice distortion is effectively increased, and the solid solution strengthening effect is generated. The application advantages of V in the combustion chamber and the components of the gas turbine for the aero-engines, the ground and the warship are particularly reflected in the aspects that V can reduce the expansion coefficient of the alloy and improve the heat conductivity of the alloy, the low expansion coefficient is beneficial to the stability of the shape and the size of the combustion chamber and the components thereof at high temperature, the early damage caused by expansion and contraction is prevented, the high heat conductivity is beneficial to the heat dissipation of the combustion chamber and the components thereof, the heat exchange between the gas cooling medium and the body of the combustion chamber is particularly accelerated, and the temperature of the combustion chamber and the components thereof is reduced. On the basis of experimental study, the invention discovers that the combined addition of V and Al has obvious effect on improving the strength of the nickel-based wrought superalloy at the medium temperature of 700 ℃, and the optimal range of the V content exists: 0.8 to 1.5 percent. The effect of increasing the medium temperature strength is not obvious when the content of V is too low, and the medium temperature plasticity and the room temperature plasticity of the alloy are reduced when the content of V is too high. Therefore, the content of the element V is controlled to be in the range of 0.8-1.5% in the embodiment of the invention.
In some embodiments, preferably, the mass percent content of Al, nd, and V satisfies the relationship 0.92% < al+2.8nd—0.6v <1.43%. Further preferably, the mass percentage content of Al, nd and V satisfies the relation 0.94% < Al+2.8Nd-0.6V <1.39%.
In the embodiment of the invention, the mass percentage of Al, nd and V is further optimized to meet the relation of 0.92% < Al+2.8Nd-0.6V <1.43%, the synergistic effect of Al, nd and V can be exerted to the greatest extent, and the prepared high-temperature alloy has more excellent comprehensive performance and can meet the design and use requirements of advanced aeroengines and gas turbines.
The embodiment of the invention also provides application of the low-density nickel-based superalloy in an aeroengine. The low-density nickel-based superalloy in the embodiment of the invention meets the design and use requirements of an advanced aeroengine and can be applied to precision equipment of the advanced aeroengine.
The embodiment of the invention also provides application of the low-density nickel-base superalloy in a gas turbine. The low-density nickel-based superalloy in the embodiment of the invention meets the design and use requirements of a gas turbine, and can be applied to precise equipment of the gas turbine.
The embodiment of the invention also provides a preparation method of the low-density nickel-based superalloy, which comprises the following steps:
(1) Adding the raw materials into a vacuum induction melting furnace according to the proportion, and heating to 1550-1650 ℃ for refining;
(2) Cooling to 1450-1550 ℃ for casting to form a high-temperature alloy cast ingot;
(3) And (3) carrying out heat treatment on the high-temperature alloy cast ingot obtained in the step (2) for 20-40 h at 800-1000 ℃.
According to the preparation method of the low-density nickel-based superalloy, the prepared low-density nickel-based superalloy has excellent room temperature tensile property, long service life, lower density, no hot welding or forging crack formation, and meets the design and use requirements of an advanced aeroengine and a gas turbine; the preparation method is simple, reduces the energy consumption, shortens the production period, improves the production efficiency, and is suitable for popularization and application in industrial production.
In some embodiments, preferably, in the step (1), the high temperature refining time is 20 to 40 minutes.
In the embodiment of the invention, the time of high-temperature refining is optimized, and the refining aims at finishing deoxidation, degassing and impurity removal, further purifying the alloy, adjusting the alloy components and leading the alloy to have more excellent performance.
The present invention will be described in detail with reference to examples.
Example 1
(1) Adding the raw materials into a vacuum induction melting furnace according to the proportion, and heating to 1550 ℃ for high-temperature refining, wherein the time of the high-temperature refining is 30min;
(2) Cooling to 1450 ℃ for casting to form a high-temperature alloy cast ingot;
(3) And (3) carrying out heat treatment on the high-temperature alloy cast ingot obtained in the step (2) for 20 hours at the temperature of 1000 ℃.
The alloy composition obtained in example 1 is shown in Table 1 and the properties are shown in Table 2.
Examples 2-8 were prepared in the same manner as in example 1, except that the alloy compositions were different, and the alloy compositions obtained in examples 2-8 were shown in Table 1, and the properties were shown in Table 2.
Example 9
Example 9 was prepared in the same manner as in example 1, except that the alloy composition was 0.732% Al+2.8Nd-0.6V, and the alloy composition obtained in example 9 was shown in Table 1 and the properties were shown in Table 2.
Example 10
Example 10 was prepared in the same manner as in example 1, except that the alloy composition was 1.452% Al+2.8Nd-0.6V, and the alloy composition obtained in example 10 was shown in Table 1 and the properties were shown in Table 2.
Example 11
Example 11 was prepared in the same manner as in example 1, except that the alloy composition was different, and no element V was contained, the alloy composition obtained in example 11 was shown in Table 1, and the properties were shown in Table 2.
Comparative example 1
Comparative example 1 was the same as the preparation method of example 1, except that the alloy composition contained 0.5% by mass of element W, and the alloy composition obtained in comparative example 1 was shown in table 1, and the properties were shown in table 2.
Comparative example 2
Comparative example 2 was the same as the preparation method of example 1, except that the alloy composition contained 1.0% by mass of element W, and the alloy composition obtained in comparative example 2 was shown in table 1, and the properties were shown in table 2.
Comparative example 3
Comparative example 3 was the same as in example 1 except that the alloy composition contained 0.6 mass% of Nb as an element, and the alloy composition obtained in comparative example 3 was shown in table 1 and the properties were shown in table 2.
Comparative example 4
Comparative example 4 was prepared in the same manner as in example 1 except that the alloy composition contained 1.2 mass% of Nb, and the alloy composition obtained in comparative example 4 was shown in Table 1, and the properties were shown in Table 2.
Comparative example 5
Comparative example 5 was the same as the preparation method of example 1, except that the content of the element V in the alloy composition was 1.8%, and the alloy composition obtained in comparative example 5 was shown in Table 1, and the properties were shown in Table 2.
Comparative example 6
Comparative example 6 was the same as the preparation method of example 1, except that the alloy composition contained no element Nd, and the alloy composition obtained in comparative example 6 was shown in table 1, and the properties were shown in table 2.
Comparative example 7
Comparative example 7 was the same as the production method of example 1, except that the content of elemental Nd in the alloy composition was 0.23%, and the alloy composition obtained in comparative example 7 was shown in table 1, and the properties were shown in table 2.
TABLE 1
Note that: the contents of the elements in the table are in wt%.
TABLE 2
Note that: 1.τ is the lasting life of the aging state alloy at 89MPa and 927 ℃, and δ is the lasting elongation after breaking of the aging state alloy at 89MPa and 927 ℃;
2、R p0.2 high temperature tensile yield strength at 700 ℃ and R as ageing state alloy m The high-temperature tensile strength of the aging alloy at 700 ℃, and the elongation after the high-temperature tensile breaking of the aging alloy at 700 ℃ is A;
3. the detection conditions of the forging cracks are as follows: 10kg of small steel ingots are forged in the radial direction at a rolling reduction of 30%, and whether cracks appear on the surfaces of the steel ingots or not is observed;
4. the detection conditions of the welding cracks are as follows: after welding, the welded joint surface was observed under an optical microscope.
5. Al+2.8Nd-0.6V in wt% in the table.
As can be seen from the data in tables 1 and 2, the nickel-based superalloy prepared by the embodiment of the invention with the content of each element controlled has the service life of more than 280 hours basically under the conditions of 89MPa and 927 ℃, the elongation after permanent break under the conditions of 89MPa and 927 ℃ can reach more than 25%, the high-temperature tensile yield strength at 700 ℃ is far higher than 652MPa, the high-temperature tensile strength at 700 ℃ is also higher than 836MPa, and the density of the alloy is lower than 8.25g/cm 3 The alloy has lighter weight, no crack after welding and forging, and better processability.
Comparative examples 1 and 2 were in which element W was added to the alloy, the addition amount of element W in comparative example 1 was 0.5%, the addition amount of element W in comparative example 2 was 1.0%, and the density of the alloy rose to 8.32g/cm after 0.5% W was added to the alloy due to the higher density of W 3 And as the content of the element W increases, the density of the alloy continuously increases to 8.38g/cm 3 The use requirements cannot be met.
Comparative examples 3 and 4 were alloys in which element Nb was added in an amount of 0.6% in comparative example 3 and in an amount of 1.2% in comparative example 4, and the element Nb improved high temperature mechanical properties such that the alloy had a high temperature tensile yield strength of 706MPa at 700 c and a high temperature tensile strength of 872MPa at 700 c, but too much Nb impaired weldability and resulted in the occurrence of crack defects during welding.
Comparative example 5 the amount of the element V was adjusted, and the amount of the element V in comparative example 5 was 1.8%, V produced a solid solution strengthening effect, but when the content was too high, the medium temperature plasticity and room temperature plasticity of the alloy were lowered. In this comparative example, the content of the element V was too high, resulting in a decrease in elongation to 22% after elongation at 700 ℃ high temperature stretch-break of the aged alloy, and cracking after forging, and deterioration in workability.
The comparative examples 6 and 7 have the amount of Nd adjusted, the comparative example 6 does not use Nd, the Nd can play a role in improving the high-temperature long-lasting life and creep resistance of the alloy, and the comparative example does not add Nd, so that the long-lasting life of the alloy is reduced to 192 hours under the conditions of 89MPa and 927 ℃; in comparative example 7, the amount of Nd was 0.23%, and when the amount was too large, the hot workability was impaired, forging cracks were caused, and large-sized inclusions were formed, resulting in deterioration of the overall properties of the alloy.
For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While the above embodiments have been shown and described, it should be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations of the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the invention.
Claims (8)
1. A low density nickel-base superalloy comprising: c:0.04-0.08%, cr:18.00-20.50%, co:9.10-11.00%, mo:8.10-9.00%, al:1.38-1.65%, ti:1.9-2.3%, zr:0-0.02%, nd:0.07-0.15%, B:0.004-0.01% and V: 0.8-1.5%, and the balance nickel and unavoidable impurities, wherein the mass percentage of Al, nd and V satisfies the relation 0.92% < Al+2.8Nd-0.6V <1.43%.
2. The low-density nickel-base superalloy of claim 1, wherein the V is 0.86-1.43 wt%.
3. The low density nickel-base superalloy of claim 1, wherein the mass percent of Al, nd, and V satisfy the relationship 0.94% < al+2.8nd-0.6v <1.39%.
4. The low density nickel-base superalloy of claim 1, wherein the low density nickel-base superalloy comprises: c:0.05-0.068%, cr:18.50-20.50%, co:9.15-9.8%, mo:8.10-9.00%, al:1.40-1.62%, ti:2.12-2.25%, zr:0-0.02%, nd:0.075-0.15%, B:0.004-0.009% and V: 0.8-1.5%, and the balance being nickel and unavoidable impurities, in mass percent.
5. Use of the low-density nickel-base superalloy of any of claims 1-4 in an aircraft engine.
6. Use of the low-density nickel-base superalloy of any of claims 1-4 in a gas turbine.
7. A method for preparing the low-density nickel-base superalloy as claimed in any of claims 1 to 4, comprising the steps of:
(1) Adding the raw materials into a vacuum induction melting furnace according to the proportion, and heating to 1550-1650 ℃ for refining;
(2) Cooling to 1450-1550 ℃ for casting to form a high-temperature alloy cast ingot;
(3) And (3) performing heat treatment on the high-temperature alloy cast ingot obtained in the step (2) for 20-40 h at 800-1000 ℃.
8. The method for producing a low-density nickel-base superalloy according to claim 7, wherein in the step (1), the refining time is 20 to 40 minutes.
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