CN115418531A - Low-density nickel-based high-temperature alloy and preparation method and application thereof - Google Patents
Low-density nickel-based high-temperature alloy and preparation method and application thereof Download PDFInfo
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- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 117
- 239000000956 alloy Substances 0.000 title claims abstract description 117
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 99
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 49
- 238000002360 preparation method Methods 0.000 title abstract description 12
- 239000012535 impurity Substances 0.000 claims abstract description 10
- 229910000601 superalloy Inorganic materials 0.000 claims description 22
- 229910052720 vanadium Inorganic materials 0.000 claims description 12
- 238000007670 refining Methods 0.000 claims description 10
- 238000010438 heat treatment Methods 0.000 claims description 8
- 238000003723 Smelting Methods 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 230000006698 induction Effects 0.000 claims description 4
- 239000002994 raw material Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 3
- 238000003466 welding Methods 0.000 abstract description 17
- 238000005242 forging Methods 0.000 abstract description 9
- 230000000052 comparative effect Effects 0.000 description 33
- 239000000203 mixture Substances 0.000 description 24
- 239000007789 gas Substances 0.000 description 12
- 230000000694 effects Effects 0.000 description 9
- 238000013461 design Methods 0.000 description 8
- 238000005728 strengthening Methods 0.000 description 8
- 230000015572 biosynthetic process Effects 0.000 description 7
- 230000007797 corrosion Effects 0.000 description 7
- 238000005260 corrosion Methods 0.000 description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- 230000006378 damage Effects 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 229910000831 Steel Inorganic materials 0.000 description 5
- 230000032683 aging Effects 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000010959 steel Substances 0.000 description 5
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 4
- 238000004519 manufacturing process Methods 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
- 230000007547 defect Effects 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 229910052742 iron Inorganic materials 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 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
- 238000005336 cracking Methods 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 230000003009 desulfurizing effect Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000009776 industrial production Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 239000011159 matrix material Substances 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
- 230000009471 action Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 229910001566 austenite Inorganic materials 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
- 230000006866 deterioration Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
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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%
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- 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
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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
- C22C19/056—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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- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
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Abstract
The invention belongs to the technical field of alloys, and particularly relates to a low-density nickel-based high-temperature alloy and a preparation method and application thereof. The invention provides a low-density nickel-based high-temperature alloy 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 percent of the total weight of the alloy, and the balance of nickel and inevitable impurities in percentage by mass. The alloy has the advantages of low density, excellent endurance life and high-temperature tensile property at 700 ℃, and no crack is formed in welding and forging, so that the use requirement is met.
Description
Technical Field
The invention belongs to the technical field of alloys, and particularly relates to a low-density nickel-based high-temperature alloy, and a preparation method and application thereof.
Background
The high-temperature alloy is a metal material which takes iron, nickel and cobalt as the base and can work for a long time at a high temperature of more than 600 ℃ under the action of certain stress, and has the comprehensive properties of higher high-temperature strength, good oxidation resistance and corrosion resistance, good fatigue property, good fracture toughness and the like. The high-temperature alloy is a single austenite structure, and has good structure stability and use reliability at various temperatures. Then, a superalloy having a high strength and good oxidation and fuel gas corrosion resistance in a range of 650 to 1000 ℃ with nickel as a base (the content is generally more than 50%) is called a nickel-based superalloy (hereinafter, referred to as "nickel-based superalloy").
The nickel-based high-temperature alloy is the most widely applied alloy with the highest high-temperature strength in the high-temperature alloys. The nickel-based alloy has the main reasons that more alloy elements can be dissolved in the nickel-based alloy, and better structural stability can be kept; secondly, can form a coherent order 3 The B-type intermetallic compound effectively strengthens the alloy and obtains higher high-temperature strength than the iron-based high-temperature alloy and the cobalt-based high-temperature alloy; third, nickel base alloy tool containing chromiumHas better oxidation resistance and fuel gas corrosion resistance than the iron-based high-temperature alloy.
Disclosure of Invention
The present invention is based on the discovery and recognition by the inventors of the following facts and problems:
the nickel-based high-temperature alloy refers to a high-temperature alloy which takes nickel as a matrix (the content is generally more than 50 percent) and has higher strength and good oxidation resistance and fuel gas corrosion resistance in the temperature range of 650-1000 ℃. Although the existing nickel-based alloy has better hot corrosion resistance, the nickel-based superalloy in the prior art cannot meet the use requirement along with the higher and higher high temperature resistance requirement of various industries on the high temperature resistant alloy, and the nickel-based superalloy with higher temperature resistance needs to be prepared to meet the use requirement.
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. To this end, embodiments of the present invention provide a low-density nickel-based superalloy having a low density, an excellent long life, and a high temperature tensile property of 700 ℃, and which is free from crack formation during welding and forging, satisfying the use requirements.
The low-density nickel-based high-temperature alloy 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 percent of the total weight of the alloy, and the balance of nickel and inevitable impurities in percentage by mass.
1, in the embodiment of the invention, no W element is added, the solid solution strengthening effect of W in the nickel-based high-temperature alloy is obvious, but W is an element for accelerating high-temperature corrosion, and harmful delta phase is formed in long-term service, so that the strength and the toughness of the alloy are reduced, and in addition, the density of W is higher and is 19.25g/cm 3 Considering that the alloy in the embodiment of the present invention is mainly used in aircraft engines and gas turbines, the lighter the material is, the better the material is, so that W is not added to the alloy in the embodiment of the present invention; 2. in the embodiment of the invention, no Nb element is added, nb is a forming element of a strengthening phase gamma', and the content of Nb is increasedThe amount of gamma 'is increased, the high-temperature creep and the endurance performance are improved, but too much gamma' can deteriorate the welding performance and damage the processing performance, in addition, nb can be combined with C to form MC type carbide to block the growth of a crystal boundary and the sliding of the crystal boundary at high temperature, so as to play a role in improving the high-temperature mechanical performance, but Nb can simultaneously form large-particle MC type carbide to be unfavorable to the mechanical performance of the alloy, in addition, too much Nb can damage the welding performance, so that the strain aging cracking sensitivity of the alloy is enhanced, the welding crack defect is easily generated, the function of Nb is comprehensively considered, and Nb is not added in the embodiment of the invention; 3. in the embodiment of the invention, nd is added, which has strong deoxidizing and desulfurizing capacities, can purify molten steel, delay the precipitation and aggregation growth of carbide along grain boundaries, further can hinder the formation and the expansion of grain boundary cracks, and can weaken or eliminate the segregation of impurity elements in the grain boundaries, thereby strengthening the grain boundaries, and playing a role in improving the high-temperature endurance life and the creep resistance of the alloy. Therefore, the embodiment of the invention controls the content of Nd within the range of 0.07-0.15%; 4. in the embodiment of the invention, the alloy has excellent room-temperature tensile property, long service life, lower density, no hot welding and forging crack formation by adopting the element composition of the design proportion, and meets the design and use requirements of advanced aeroengines and gas turbines.
In some embodiments, the low density nickel-base superalloy further comprises 0.8 to 1.5% V by weight.
In some embodiments, the V is 0.86 to 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 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 of nickel and inevitable impurities, calculated by mass percentage.
The embodiment of the invention also provides application of the low-density nickel-based high-temperature alloy in an aeroengine.
The embodiment of the invention also provides application of the low-density nickel-based high-temperature alloy in a gas turbine.
The embodiment of the invention also provides a preparation method of the low-density nickel-based high-temperature alloy, which comprises the following steps:
(1) Adding the raw materials into a vacuum induction smelting furnace according to the proportion, and heating to 1550-1650 ℃ for refining;
(2) Cooling to 1450-1550 ℃ for pouring to form a high-temperature alloy ingot;
(3) And (3) carrying out heat treatment on the high-temperature alloy ingot obtained in the step (2) at 800-1000 ℃ for 20-40 h.
The low-density nickel-based high-temperature alloy prepared by the preparation method has the advantages and technical effects that 1, the low-density nickel-based high-temperature alloy prepared by the preparation method has excellent room-temperature tensile property, long service life, low density, no heat welding and no 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, the energy consumption is reduced, the production period is shortened, the production efficiency is improved, and the preparation method is suitable for popularization and application of industrial production.
In some embodiments, in the step (1), the high-temperature refining time is 20 to 40min.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
The low-density nickel-based high-temperature alloy provided by the embodiment of the invention 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 percent of the total weight of the alloy, and the balance of nickel and inevitable impurities in percentage by mass.
In the embodiment of the invention, no W element is added, the solid solution strengthening effect of W in the nickel-based high-temperature alloy is obvious, but W is an element for accelerating high-temperature corrosion, and harmful delta phase is formed in long-term service, so that the strength and the toughness of the alloy are reduced, and in addition, the density of W is higher and is 19.25g/cm 3 Considering that the alloy in the embodiment of the invention is mainly used for aeroengines and gas turbines, the lighter the material is, the better the material is, so that W is not added in the alloy in the embodiment of the invention; in the embodiment of the invention, no Nb element is added, nb is a forming element of a strengthening phase gamma ', the quantity of gamma ' is increased along with the increase of Nb content, the high-temperature creep and the durability are improved, but too much 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 hindered 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 rather unfavorable, in addition, too much Nb can damage the welding performance, the strain aging cracking sensitivity of the alloy is enhanced, the welding crack defect is easily generated, the effect of Nb is comprehensively considered, and no Nb is added in the embodiment of the invention; in the embodiment of the invention, nd is added, which has strong deoxidizing and desulfurizing capacities, can purify molten steel, delay the precipitation and aggregation growth of carbide along grain boundaries, further can hinder the formation and the expansion of grain boundary cracks, and can weaken or eliminate the segregation of impurity elements in the grain boundaries, thereby strengthening the grain boundaries, and playing a role in improving the high-temperature endurance life and the creep resistance of the alloy. Therefore, the embodiment of the present invention controls the Nd content to be in the range of 0.07 to 0.15%. In the examples of the present inventionThe alloy is composed of elements with designed proportion, so that the alloy has excellent room temperature tensile property, long service life, lower density, no heat welding and forging crack formation, and meets the design and use requirements of advanced aeroengines and gas turbines.
In some embodiments, preferably, the low density nickel-based 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 of nickel and inevitable impurities, calculated by mass percentage.
In some embodiments, preferably, the low-density nickel-based superalloy further comprises 0.8 to 1.5 mass% of V. More preferably, the content of V is 0.86-1.43% by mass.
In the embodiment of the invention, the element V is added into the alloy, the V is a strong carbide and a gamma' forming element, and the V can replace Ni 3 The position of Al in Al (gamma') improves the stability of the alloy, and V can be dissolved in a matrix in a solid mode, so that the lattice distortion is effectively increased, and the solid solution strengthening effect is generated. The application advantages of the V in the combustion chambers and parts of the gas turbines for aircraft engines, ground and ships are particularly embodied in two aspects that the V can reduce the expansion coefficient of the alloy and improve the heat conductivity of the alloy, the low expansion coefficient is beneficial to keeping the stability of the shapes and the sizes of the combustion chambers and the parts thereof at high temperature and preventing the early damage caused by expansion with heat and contraction with cold, the high heat conductivity is beneficial to heat dissipation of the combustion chambers and the parts thereof, particularly the heat exchange between the steam cooling medium and the body of the combustion chambers is accelerated, and the reduction of the temperature of the combustion chambers and the parts thereof is facilitated. On the basis of experimental research, the invention finds that the combined addition of V and Al has obvious effect on improving the medium temperature 700 ℃ strength of the nickel-based wrought superalloy, and the content of V has the optimum range: 0.8 to 1.5 percent. Too low a content of V does not have an obvious effect of improving the medium-temperature strength, and too high a content of V reduces the medium-temperature plasticity and room-temperature plasticity of the alloy. Therefore, in the examples of the present invention, the content of element V is controlled to be in the range of 0.8 to 1.5%.
In some embodiments, it is preferable that the Al, nd, and V are contained in mass percentages satisfying the relationship 0.92% < Al +2.8 Nd-0.6v-1.43%. Further preferably, the mass percentages of Al, nd and V satisfy the relation 0.94% < Al +2.8 Nd-0.6V-Ap < -1.39%.
In the embodiment of the invention, the mass percentage of Al, nd and V is preferably more than 0.92% < Al +2.8Nd-0.6V <1.43%, the synergistic effect of Al, nd and V can be exerted to the maximum extent, and the prepared high-temperature alloy has more excellent comprehensive performance and can meet the requirements of design and use of advanced aeroengines and gas turbines.
The embodiment of the invention also provides application of the low-density nickel-based high-temperature alloy in an aeroengine. The low-density nickel-based high-temperature alloy in the embodiment of the invention meets the design and use requirements of advanced aero-engines, and can be applied to precision equipment of the advanced aero-engines.
The embodiment of the invention also provides application of the low-density nickel-based high-temperature alloy in a gas turbine. The low-density nickel-based high-temperature alloy in the embodiment of the invention meets the design and use requirements of a gas turbine, and can be applied to precision equipment of the gas turbine.
The embodiment of the invention also provides a preparation method of the low-density nickel-based high-temperature alloy, which comprises the following steps:
(1) Adding the raw materials into a vacuum induction smelting furnace according to the proportion, and heating to 1550-1650 ℃ for refining;
(2) Cooling to 1450-1550 ℃ for pouring to form a high-temperature alloy ingot;
(3) And (3) carrying out heat treatment on the high-temperature alloy ingot obtained in the step (2) at 800-1000 ℃ for 20-40 h.
According to the preparation method of the low-density nickel-based high-temperature alloy, the prepared low-density nickel-based high-temperature alloy has excellent room-temperature tensile property, long service life and low density, does not have hot welding and forged crack formation, and meets the design and use requirements of advanced aeroengines and gas turbines; the preparation method is simple, reduces energy consumption, shortens production period, improves production efficiency, and is suitable for popularization and application of industrial production.
In some embodiments, preferably, in the step (1), the high-temperature refining time is 20 to 40min.
In the embodiment of the invention, the high-temperature refining time is optimized, and the refining aims to complete deoxidation, degassing and impurity removal, further purify the alloy, adjust the alloy components and enable the performance of the alloy to be more excellent.
The present invention will be described in detail with reference to examples.
Example 1
(1) Adding the raw materials into a vacuum induction smelting furnace according to the proportion, heating to 1550 ℃ for high-temperature refining, wherein the high-temperature refining time is 30min;
(2) Cooling to 1450 ℃ for pouring to form a high-temperature alloy ingot;
(3) And (3) carrying out heat treatment on the high-temperature alloy ingot obtained in the step (2) at 1000 ℃ for 20h.
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 according to the same method as in example 1, except that the alloy compositions were different, and the alloy compositions obtained in examples 2-8 are shown in Table 1 and the properties are shown in Table 2.
Example 9
Example 9 was prepared in the same manner as in example 1 except that the alloy composition was changed to 0.732% by weight of Al +2.8Nd-0.6V, and the alloy composition and properties of example 9 are shown in Table 1 and Table 2, respectively.
Example 10
Example 10 was prepared in the same manner as in example 1 except that the alloy composition was changed to 1.452% by adding Al +2.8Nd-0.6V, the alloy composition obtained in example 10 is shown in Table 1, and the properties are shown in Table 2.
Example 11
Example 11 was prepared in the same manner as example 1 except that the alloy composition was changed to the one shown in Table 1, and the alloy composition and properties of example 11 were shown in Table 2.
Comparative example 1
Comparative example 1 was prepared in the same manner as in example 1 except that the alloy composition contained 0.5% by mass of element W, the alloy composition obtained in comparative example 1 is shown in table 1, and the properties are shown in table 2.
Comparative example 2
Comparative example 2 was prepared in the same manner as in example 1 except that the alloy composition contained 1.0 mass% of element W, and the alloy composition obtained in comparative example 2 is shown in table 1 and the properties are shown in table 2.
Comparative example 3
Comparative example 3 is prepared in the same manner as in example 1 except that 0.6 mass% of Nb is contained in the alloy composition, and the alloy composition and properties obtained in comparative example 3 are shown in table 1 and table 2, respectively.
Comparative example 4
Comparative example 4 was prepared in the same manner as in example 1 except that the element Nb was contained in the alloy composition in a mass fraction of 1.2%, the alloy composition obtained in comparative example 4 is shown in table 1, and the properties are shown in table 2.
Comparative example 5
Comparative example 5 was prepared in the same manner as in example 1 except that the content of element V in the alloy composition was 1.8%, the alloy composition obtained in comparative example 5 is shown in table 1, and the properties are shown in table 2.
Comparative example 6
Comparative example 6 was prepared in the same manner as in example 1 except that the element Nd was not contained in the alloy composition, and comparative example 6 produced an alloy composition shown in table 1 and properties shown in table 2.
Comparative example 7
Comparative example 7 was prepared in the same manner as in example 1 except that the content of Nd element in the alloy composition was 0.23%, the alloy composition obtained in comparative example 7 is shown in table 1, and the properties are shown in table 2.
TABLE 1
Note: the contents of the elements in the table are in wt%.
TABLE 2
Note: 1. tau is the endurance life of the alloy in the aging state under the conditions of 89MPa and 927 ℃, and delta is the endurance post-fracture elongation of the alloy in the aging state under the conditions of 89MPa and 927 ℃;
2、R p0.2 the alloy in an aging state has the tensile yield strength R at high temperature of 700 DEG C m The tensile strength at high temperature of 700 ℃ of the aged alloy, and A is the elongation after tensile fracture at high temperature of 700 ℃ of the aged alloy;
3. the detection conditions of the forging cracks are as follows: a 10kg ingot type small steel ingot is forged in the radial direction at a reduction ratio of 30%, and whether cracks appear on the surface of the steel ingot 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. In the table, al +2.8Nd-0.6V is in wt%.
As can be seen from the data in tables 1 and 2, the nickel-based superalloy prepared by controlling the content of each element in the embodiment of the invention basically has the service life of more than 280h under the conditions of 89MPa and 927 ℃, the elongation after permanent fracture 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 steel has lighter weight, no crack after welding and forging, and better processing performance.
Comparative examples 1 and 2 were made by adding element W to the alloy, the amount of element W added in comparative example 1 was 0.5%, and the amount of element W added in comparative example 2 was 1.0%, and since the density of W was large, the density of the alloy increased to 8.32g/cm after 0.5% W was added to the alloy 3 And as the content of the element W increases, the density of the alloy continuously increases to 8.38g/cm 3 And the use requirements cannot be met.
In comparative examples 3 and 4, the element Nb is added into the alloy, the addition amount of the element Nb in the comparative example 3 is 0.6 percent, the addition amount of the element Nb in the comparative example 4 is 1.2 percent, and the element Nb can improve the high-temperature mechanical property, so that the high-temperature tensile yield strength at 700 ℃ of the alloy reaches 706MPa, the high-temperature tensile strength at 700 ℃ reaches 872MPa, but excessive Nb can damage the welding performance, and the crack defect is caused during welding.
Comparative example 5 in which the amount of element V is adjusted to 1.8%, V can produce a solid solution strengthening effect, but when the content is too high, the intermediate temperature plasticity and room temperature plasticity of the alloy are reduced. In the comparative example, too high a content of element V resulted in a reduction of elongation to 22% after elongation at high temperature tensile break at 700 ℃ of the aged alloy, and cracks were generated after forging, and workability was deteriorated.
The use amount of the element Nd is adjusted in comparative examples 6 and 7, the element Nd is not used in the comparative example 6, the element Nd can play a role in improving the high-temperature endurance life and the creep resistance of the alloy, and the element Nd is not added in the comparative example, so that the endurance life of the alloy is reduced to 192h 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, hot workability was impaired, forging cracks were caused, and large-sized inclusions were formed, resulting in deterioration of the overall properties of the alloy.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer 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, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although the above embodiments have been shown and described, it should be understood that they are exemplary and should not be construed as limiting the present invention, and that many changes, modifications, substitutions and alterations to the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the present invention.
Claims (10)
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% and B:0.004-0.01 percent of the total weight of the alloy, and the balance of nickel and inevitable impurities in percentage by mass.
2. The low density nickel-base superalloy as in claim 1, further comprising 0.8 to 1.5 mass% V.
3. The low-density nickel-base superalloy according to claim 2, wherein the V is 0.86 to 1.43 mass%.
4. The low-density nickel-base superalloy as in claim 2, wherein the mass percentage of Al, nd, and V satisfies the relation 0.92% < Al +2.8Nd-0.6v < -1.43%.
5. The low-density nickel-base superalloy according to claim 4, wherein the mass percentage of Al, nd, and V satisfies the relation of 0.94% < Al +2.8 Nd-0.6V-Ap 1.39%.
6. The low density nickel-base superalloy as in claim 1, comprising: 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 of nickel and inevitable impurities, calculated by mass percentage.
7. Use of the low density nickel base superalloy of any of claims 1 to 6 in an aircraft engine.
8. Use of the low density nickel base superalloy of any of claims 1 to 6 in a gas turbine.
9. A method for preparing a low density nickel base superalloy as in any of claims 1 to 6, comprising the steps of:
(1) Adding the raw materials into a vacuum induction smelting furnace according to the proportion, and heating to 1550-1650 ℃ for refining;
(2) Cooling to 1450-1550 ℃ for pouring to form a high-temperature alloy ingot;
(3) And (3) carrying out heat treatment on the high-temperature alloy ingot obtained in the step (2) at 800-1000 ℃ for 20-40 h.
10. The method for preparing a low-density nickel-base superalloy according to claim 9, wherein in the step (1), the high-temperature refining time is 20-40 min.
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| WO2022100169A1 (en) * | 2020-11-12 | 2022-05-19 | 中国联合重型燃气轮机技术有限公司 | Creep-resistant, long-service-life, nickel-based deformation superalloy and method for preparation thereof and application thereof |
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