CN117684047A - High-temperature alloy for turbine blade of gas turbine, and preparation method and application thereof - Google Patents
High-temperature alloy for turbine blade of gas turbine, and preparation method and application thereof Download PDFInfo
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- 229910052804 chromium Inorganic materials 0.000 claims abstract description 22
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- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract description 21
- 239000012535 impurity Substances 0.000 claims abstract description 20
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- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 20
- 239000010937 tungsten Substances 0.000 claims abstract description 20
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- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 19
- 239000010941 cobalt Substances 0.000 claims abstract description 19
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910052746 lanthanum Inorganic materials 0.000 claims abstract description 17
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 claims abstract description 17
- 229910052684 Cerium Inorganic materials 0.000 claims abstract description 16
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- 229910052796 boron Inorganic materials 0.000 claims abstract description 15
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Abstract
The invention provides a high-temperature alloy for a turbine blade of a gas turbine, and a preparation method and application thereof, and belongs to the technical field of nickel alloy materials. The invention provides a high-temperature alloy for a turbine blade of a gas turbine, which comprises the following element components in percentage by mass: 0.001-0.1% of carbon, 1-2.9% of rhenium, 0.2-1.5% of molybdenum, 6-8% of aluminum, 3-7% of tantalum, 6-10% of chromium, 6-10% of cobalt, 3-5% of tungsten, 0.003-0.006% of boron, 0.1-0.2% of hafnium, 0.001% or more of yttrium+lanthanum and 0.01% or less, 0.005% or less of cerium, 0.04% or less of impurity elements and the balance of nickel. The high-temperature alloy for the turbine blade of the gas turbine has high strength and good corrosion resistance and oxidation resistance, and can be applied to the turbine blade of the variable cycle gas engine with the service temperature of more than 1000 ℃.
Description
Technical Field
The invention relates to the technical field of nickel alloy materials, in particular to a high-temperature alloy for a turbine blade of a gas turbine, and a preparation method and application thereof.
Background
With the development of ship technology, the development of ship power is in great demand. Currently, national gas turbines are the primary choice for ship power. The turbine blade is the most severe service environment in the gas turbine, high working temperature (more than 1100 ℃) and high centrifugal force caused by high rotating speed, and Cl caused by marine environment - Ion corrosion, etc., can reduce the useful life of the turbine blade. Therefore, turbine blade materials of ship gas turbines require both high enough high temperature resistance and certain environmental resistance to cope with the harsh corrosive environment of the ocean.
In order to improve the environmental resistance (oxidation resistance and hot corrosion resistance) of the alloy, cr, W, mo, nb, ti, al, ta and other elements are generally added in the design process of the high-temperature alloy, but the mutual influence among the alloy elements restricts the further application of the high-temperature alloy, meanwhile, trace elements in the high-temperature alloy are divided into harmful elements, beneficial elements and some elements which are not proved to be harmful or beneficial, the occurrence forms of the elements in the alloy are difficult to confirm, and the research on the effect of the elements on the alloy is difficult.
Therefore, development of a high-temperature alloy for a turbine blade of a gas turbine with long service life, oxidation resistance and hot corrosion resistance is a technical problem to be solved in the art.
Disclosure of Invention
The invention aims to provide a high-temperature alloy for a turbine blade of a gas turbine, and a preparation method and application thereof.
In order to achieve the above object, the present invention provides the following technical solutions:
a superalloy for a gas turbine blade, comprising, in mass percent: 0.001-0.1% of carbon, 1-2.9% of rhenium, 0.2-1.5% of molybdenum, 6-8% of aluminum, 3-7% of tantalum, 6-10% of chromium, 6-10% of cobalt, 3-5% of tungsten, 0.003-0.006% of boron, 0.1-0.2% of hafnium, 0.001% or more of yttrium+lanthanum and 0.01% or less, 0.005% or less of cerium, 0.04% or less of impurity elements and the balance of nickel.
Preferably, the impurity element includes one or more of H, O, N, S, zn, ga, ge, as, br, rb, sr, ru, rh, cd, in, sn, sb, ca, cs, ba, bi, pr, ho, er, tm, lu, os, ir, au, hg, th, I, cl, nd, U, K, yb, li, pt and Pd;
the content of H is less than or equal to 1ppm;
the content of O, N and S is independently less than or equal to 6ppm;
the mass content of Zn, ga, ge, as, br, rb, sr, ru, rh, cd, in, sn, sb, ca, cs, ba, bi, pr, ho, er, tm, lu, os, ir, au, hg, th, I, cl, nd, U, K, yb, li, pt and Pd is independently less than or equal to 0.002 percent.
The invention also provides a preparation method of the high-temperature alloy for the turbine blade of the gas turbine, which comprises the following steps:
feeding according to the sequence of partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, rhenium, chromium and residual nickel, sequentially melting and refining, and sequentially adding aluminum, residual carbon, hafnium and nickel-boron intermediate alloy to obtain alloy melt;
and in the argon atmosphere, sequentially adding a desulfurizing agent, yttrium, nickel-lanthanum intermediate alloy and nickel-cerium intermediate alloy into the alloy melt, deoxidizing and desulfurizing, and then pouring to obtain the high-temperature alloy for the turbine blade of the gas turbine.
Preferably, both the melting and refining are performed under vacuum;
the vacuum degree of the vacuum is less than 10 -1 Pa。
Preferably, the refining comprises a first heat preservation after a first temperature rise, a second heat preservation after a second temperature rise and a third heat preservation after a third temperature rise which are sequentially carried out;
the temperature of the first heat preservation is 1490-1510 ℃, and the heat preservation time is 9-11 min;
the temperature of the second heat preservation is 1545-1555 ℃, and the heat preservation time is 18-22 min;
the temperature of the third heat preservation is 1595-1605 ℃, and the heat preservation time is 28-32 min.
Preferably, the temperature rising rate of the second temperature rising is 4-6 ℃/min;
and the temperature rising rate of the third temperature rising is 2-3 ℃/min.
Preferably, the temperature of the product obtained by refining is 1470-1490 ℃.
Preferably, the pressure of argon in the argon atmosphere is 1900-2100 Pa.
Preferably, the temperature of the deoxidation and desulfurization is 1515-1525 ℃, and the heat preservation time is 3-5 min.
The invention also provides application of the high-temperature alloy for the gas turbine blade or the high-temperature alloy for the gas turbine blade prepared by the preparation method in the technical scheme in the gas turbine blade with the use temperature of more than 1000 ℃.
The invention provides a high-temperature alloy for turbine blades of a gas turbine, which comprises the following element components in percentage by mass: 0.001-0.1% of carbon, 1-2.9% of rhenium, 0.2-1.5% of molybdenum, 6-8% of aluminum, 3-7% of tantalum, 6-10% of chromium, 6-10% of cobalt, 3-5% of tungsten, 0.003-0.006% of boron, 0.1-0.2% of hafnium, 0.001% or more of yttrium+lanthanum and 0.01% or less, 0.005% or less of cerium, 0.04% or less of impurity elements and the balance of nickel. According to the high-temperature alloy for the turbine blade of the gas turbine, chromium is added to form a solid solution state, chromium exists in a matrix, a small amount of carbide is generated, and the oxidation resistance and the hot corrosion resistance of the alloy are improved; the high-temperature performance of the alloy can be improved by adding tungsten, molybdenum, aluminum and tantalum, wherein the tantalum can increase the order degree of gamma' phase, improve the solid solution strengthening capability of gamma phase, and the molybdenum is beneficial to improving the mismatch degree, achieves the interface strengthening effect, and does not cause formation of TCP to destroy the tissue stability; cobalt has good hot corrosion resistance, and can improve the structural stability and the high-temperature strength; the yttrium, lanthanum and cerium can promote the selective oxidation of Al and Cr elements, reduce the oxidation rate of the alloy, and simultaneously lead the alloy to reach the complete oxidation resistance at 1100 ℃ in a composite addition form of the yttrium and lanthanum elements; the rhenium obviously reduces the growth rate of the gamma prime strengthening phase, is biased to the matrix, leads the gamma/gamma prime mismatch degree to become more negative and is beneficial to forming high densityDislocation net, can also form the short-range ordered atomic group in the basal body, hinder dislocation movement, raise the intensity of alloy; carbon and boron are used as strengthening elements between grain boundaries and dendrites, can be biased to the grain boundaries and dendrites to serve as gap elements to fill gaps between the areas, slow diffusion so as to reduce the cracking tendency between the grain boundaries and the dendrites, form carbide and boride, strengthen the grain boundaries and the dendrites, and improve the strength of the alloy; hafnium can strengthen gamma' phase and is also a strong carbide forming element, and can prevent M 23 C 6 Or M 6 C is greatly precipitated along the grain boundary, so that the strength of the alloy is improved; by reducing the content of impurity elements, the performance of the alloy is further improved. The results of the examples show that the high-temperature alloy for the turbine blade of the gas turbine provided by the invention has complete oxidation resistance at 1100 ℃ and the oxidation rate of 0.03-0.04 g/m 2 H, the high-temperature structure stability at 1000 ℃ for 2000h is good, no TCP phase is separated out, and the hot corrosion rate is 0.04-0.05 g/(m) 2 H), high temperature tensile Strength delta at 1100 DEG C b 400-420 MPa, yield strength delta p0.2 235-265 MPa, the breaking time of high-temperature durability performance at 1100 ℃ under 158MPa is 38-45 h, and the high-cycle fatigue performance at 1120 ℃ under the maximum stress delta max Fracture cycle N at 70MPa f Is 9 to 10 multiplied by 10 6 Has high strength and good corrosion resistance and oxidation resistance.
The invention is regulated by controlling the feeding and smelting processes of raw materials, specifically, part of carbon is added in the slow melting period to react with oxygen remained in the furnace and on the surface of metal in the early slow melting process, oxygen atoms are removed, aluminum is added after refining to avoid the influence of thermite reaction on smelting, yttrium, nickel-cerium intermediate alloy and nickel-lanthanum intermediate alloy are added in the deoxidizing and desulfurizing period, the large deviation of volatile yttrium, cerium and lanthanum in the smelting process can be avoided, and meanwhile, the alloy melt can be purified.
Detailed Description
The invention provides a high-temperature alloy for turbine blades of a gas turbine, which comprises the following element components in percentage by mass: 0.001-0.1% of carbon, 1-2.9% of rhenium, 0.2-1.5% of molybdenum, 6-8% of aluminum, 3-7% of tantalum, 6-10% of chromium, 6-10% of cobalt, 3-5% of tungsten, 0.003-0.006% of boron, 0.1-0.2% of hafnium, 0.001% or more of yttrium+lanthanum and 0.01% or less, 0.005% or less of cerium, 0.04% or less of impurity elements and the balance of nickel.
The high-temperature alloy for the turbine blade of the gas turbine comprises 0.001-0.1% of carbon, preferably 0.03-0.05% of carbon, and more preferably 0.04% of carbon. In the invention, C is a strengthening element between grain boundaries and dendrites in the high-temperature alloy, and C which is biased between the grain boundaries and the dendrites can be used as a gap element to fill gaps of the areas, slow diffusion so as to reduce the cracking tendency between the grain boundaries and the dendrites, form carbide and strengthen the grain boundaries and the dendrites; by controlling the content of the carbon element within the above range, the strength of the alloy can be improved.
The high-temperature alloy for the turbine blade of the gas turbine comprises 1-2.9% of rhenium, preferably 1.5-2.8% of rhenium, and more preferably 2.5% of rhenium. In the invention, re element obviously reduces the growth rate of the gamma '-strengthening phase, and is biased to the matrix, so that the gamma/gamma' -mismatching degree becomes more negative, a dislocation network with high density is formed, short-range ordered atomic groups can be formed in the matrix, dislocation movement is blocked, and the strength of the alloy is improved; by controlling the content of rhenium element within the above range, the strength of the alloy can be improved.
The high-temperature alloy for the turbine blade of the gas turbine comprises 0.2-1.5% of molybdenum, preferably 0.3-1.4% of molybdenum, and more preferably 1% of molybdenum. In the invention, molybdenum element is beneficial to improving the degree of mismatching, achieving the effect of interface strengthening, simultaneously not causing TCP to be formed to destroy the tissue stability, and improving the high-temperature strength of the alloy by controlling the content of molybdenum element in the above range.
The high-temperature alloy for the turbine blade of the gas turbine comprises 6-8% of aluminum, preferably 6.2-7.5% of aluminum and more preferably 7% of aluminum. In the present invention, by controlling the content of aluminum element within the above-described range, it is possible to improve the high temperature performance of the alloy and avoid affecting the strength and toughness of the alloy.
The high-temperature alloy for the turbine blade of the gas turbine comprises 3-7% of tantalum, preferably 5-6.5%, and more preferably 6% of tantalum. In the invention, the tantalum element can increase the order degree of the gamma' phase, improve the solid solution strengthening capability of the gamma phase, and improve the high-temperature strength of the alloy by controlling the content of the tantalum element within the above range.
The high-temperature alloy for the turbine blade of the gas turbine comprises, by mass, 6-10% of chromium, preferably 7.5-9%, and more preferably 8.5%. In the invention, cr element exists in a matrix in a solid solution state, and a small amount of Cr element generates carbide; by controlling the content of chromium element within the above range, the oxidation resistance and hot corrosion resistance of the alloy can be improved.
The high-temperature alloy for the turbine blade of the gas turbine comprises, by mass, 6-10% of cobalt, preferably 7.5-9.5%, and more preferably 8-9%. In the invention, cobalt has good hot corrosion resistance, and the content of cobalt element is controlled within the range, so that the hot corrosion resistance of the alloy can be improved, and meanwhile, the structural stability and the high-temperature strength can be improved.
The high-temperature alloy for the turbine blade of the gas turbine comprises 3-5% of tungsten, preferably 3.5-4.5% of tungsten and more preferably 4% of tungsten. In the present invention, by controlling the content of tungsten element within the above range, the high temperature strength of the alloy can be improved.
The high-temperature alloy for the turbine blade of the gas turbine comprises 0.003-0.006% of boron, preferably 0.003-0.005% of boron. In the present invention, B is a strengthening element between grain boundaries and dendrites in a high temperature alloy, and B, which is biased between grain boundaries and dendrites, can fill gaps in these regions as a gap element, slow diffusion to reduce the tendency of cracking between grain boundaries and dendrites, and also form boride to strengthen grain boundaries and dendrites, and by controlling the content of boron element within the above-mentioned range, the strength of the alloy can be improved.
The high-temperature alloy for the turbine blade of the gas turbine comprises 0.1-0.2% of hafnium, preferably 0.12-0.17% of hafnium, and more preferably 0.15% of hafnium. In the invention, hafnium can strengthen gamma' phase and is also a very strong carbide forming element, and can resistStop M 23 C 6 Or M 6 C is precipitated in a large amount along the grain boundary, and by controlling the content of hafnium element within the above-mentioned range, the strength of the alloy can be improved.
The high-temperature alloy for the turbine blade of the gas turbine comprises, by mass, 0.001% -0.01% yttrium+lanthanum, and preferably 0.001% -0.008%. In the invention, yttrium and lanthanum can promote the selective oxidation of Al and Cr elements, reduce the oxidation rate of the alloy, and simultaneously, the yttrium and lanthanum elements are added in a compound mode, so that the alloy achieves the complete oxidation resistance at 1100 ℃, and the oxidation resistance of the alloy can be improved by controlling the content of the yttrium and lanthanum elements in the above range.
The high-temperature alloy for the turbine blade of the gas turbine comprises less than or equal to 0.005% of cerium, and preferably less than or equal to 0.004% of cerium. In the present invention, cerium promotes the selective oxidation of Al and Cr elements, reduces the oxidation rate of the alloy, and improves the oxidation resistance of the alloy by controlling the content of cerium element within the above range.
The high-temperature alloy for the turbine blade of the gas turbine comprises less than or equal to 0.04% of impurity elements by mass percent. The present invention can further improve the overall properties of the alloy by limiting the impurity element content to the above-described range.
In the present invention, the impurity element preferably includes one or more of H, O, N, S, zn, ga, ge, as, br, rb, sr, ru, rh, cd, in, sn, sb, ca, cs, ba, bi, pr, ho, er, tm, lu, os, ir, au, hg, th, I, cl, nd, U, K, yb, li, pt and Pd.
In the present invention, the content of H is preferably 1ppm or less; the content of O, N and S is preferably independently less than or equal to 6ppm; the mass content of Zn, ga, ge, as, br, rb, sr, ru, rh, cd, in, sn, sb, ca, cs, ba, bi, pr, ho, er, tm, lu, os, ir, au, hg, th, I, cl, nd, U, K, yb, li, pt and Pd is preferably independently less than or equal to 0.002%. The invention can ensure the high purity of the alloy and improve the performance of the alloy by limiting the content of impurity elements to be within the range.
The high-temperature alloy for the turbine blade of the gas turbine provided by the invention contains a large amount of environmental resistance elements Cr, can improve the oxidation resistance and hot corrosion resistance of the alloy, and also contains a plurality of high-temperature resistance elements W, mo, ti, al and Ta, so that the alloy has good structural stability and good high-temperature performance, the addition of trace elements Y, la and Ce in the alloy can promote the selective oxidation of Al and Cr elements, the oxidation rate of the alloy is reduced, the addition of carbon, boron, rhenium and hafnium can improve the strength of the alloy, the content of impurity elements is limited to be less than 0.04%, and the comprehensive performance of the alloy is further improved.
The invention also provides a preparation method of the high-temperature alloy for the turbine blade of the gas turbine, which comprises the following steps:
feeding according to the sequence of partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, rhenium, chromium and residual nickel, sequentially melting and refining, and sequentially adding aluminum, residual carbon, hafnium and nickel-boron intermediate alloy to obtain alloy melt;
and in the argon atmosphere, sequentially adding a desulfurizing agent, yttrium, nickel-lanthanum intermediate alloy and nickel-cerium intermediate alloy into the alloy melt, deoxidizing and desulfurizing, and then pouring to obtain the high-temperature alloy for the turbine blade of the gas turbine.
According to the method, partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, rhenium, chromium and residual nickel are sequentially fed, melted and refined, and then aluminum, residual carbon, hafnium and nickel-boron intermediate alloy are sequentially added to obtain alloy melt.
In the present invention, the purity of the nickel is preferably a brand purity of not less than Ni9996; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The purity of the alloy can be improved by limiting the purity of nickel to the above range.
In the invention, the purity of the cobalt is preferably the grade purity not lower than Co9995; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The purity of cobalt is limited to the above range, and the purity of the alloy can be improved.
In the present invention, the purity of the molybdenum is preferably a brand purity of not less than Mo-1; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The present invention limits the purity of molybdenum to the above-described range, and can improve the purity of the alloy.
In the present invention, the purity of the carbon is preferably a brand purity not lower than that of a spectral graphite electrode (TSG); the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The present invention can improve the purity of the alloy by limiting the purity of carbon to the above range.
In the invention, the purity of the tantalum is preferably equal to or higher than the brand purity of TD-T; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The purity of tantalum is limited to the above range, and the purity of the alloy can be improved.
In the invention, the purity of the tungsten is preferably not lower than TW-1; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The purity of the alloy can be improved by limiting the purity of tungsten to the above range.
In the present invention, the purity of rhenium is preferably no less than r99.99; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The present invention limits the purity of rhenium to the above-described range, and can improve the purity of the alloy.
In the present invention, the purity of the chromium is preferably a grade purity of not less than GCCr-1; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The present invention limits the purity of chromium to the above-described range, and can improve the purity of the alloy.
In the invention, the purity of the aluminum is preferably not lower than Al99.99; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The purity of the alloy can be improved by limiting the purity of the aluminum to the above-described range.
In the present invention, the purity of the hafnium is preferably a brand purity of not less than HHf-01; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The purity of the alloy can be improved by limiting the purity of hafnium to the above-described range.
In the present invention, the nickel-boron master alloy is preferably a nickel-boron master alloy having a boron content of 20 wt%.
The invention preferably brushes the crucible surface with a layer of ZrO prior to charging 2 And (5) sintering treatment is carried out after coating.
In the present invention, the crucible is preferably a spinel crucible. The invention limits the crucible to the above type, and can meet the requirement of high-temperature sintering.
In the present invention, the ZrO 2 The thickness of the coating is preferably 2-3 mm. The present invention is not particularly limited to the application of the coating layer, and may be performed by any operation known to those skilled in the art. The invention is characterized in that a layer of ZrO is coated on the surface of a crucible 2 The coating may increase the temperature resistance of the crucible.
In the invention, the sintering treatment process is preferably to heat up to 900 ℃ for 2 hours and then to heat up to 1200 ℃ for 2 hours after heat up to 600 ℃ for 2 hours; the temperature rising rate of each stage is independently 5 ℃/min. According to the invention, through the sintering treatment process, the crucible can be prevented from being cracked prematurely in the alloy smelting process.
The present invention preferably pretreats the alloy feed prior to addition.
In the invention, the pretreatment is preferably to sequentially polish, ultrasonically clean and dry the surface oxide skin of the alloy raw material.
In the invention, the polishing of the surface oxide skin of the alloy raw material is preferably carried out in a roller; the polishing operation of the present invention is not particularly limited, and may be performed by any operation known to those skilled in the art.
In the present invention, the solvent for ultrasonic cleaning is preferably absolute ethanol. The specific operation and parameter setting of the ultrasonic cleaning are not particularly limited, and those well known to those skilled in the art may be employed.
The present invention is not particularly limited to the equipment and parameter setting for the drying, and the alloy raw material is dried by adopting the drying operation well known in the art.
In the present invention, the partial carbon is preferably 1/2 of the total carbon content. The invention can sufficiently remove O element in the smelting process by limiting part of carbon to the above range.
In the present invention, the melting and refining are performed under vacuum; the vacuum is preferably less than 10 -1 Pa. The invention can reduce the impurity content in the alloy and improve the purity of the alloy by limiting the vacuum degree in the melting and refining process to be within the range.
In the present invention, the melting process is preferably controlled by the electric power; the setting of the electric power is preferably that the initial electric power is 80kW, the electric power is increased to 150kW after the alloy turns red, and the electric power is increased to 180kW after the alloy is completely melted. The present invention improves the purity of the alloy by setting the electric power to be in the above range, which allows better melting of the alloy, and removing the O impurity in the alloy melt.
In the present invention, the refining preferably includes a first heat preservation after a first temperature rise, a second heat preservation after a second temperature rise, and a third heat preservation after a third temperature rise, which are sequentially performed.
In the invention, the temperature of the first heat preservation is preferably 1490-1510 ℃, more preferably 1500 ℃; the heat preservation time of the first heat preservation is preferably 9-11 min, more preferably 10min; the temperature of the second heat preservation is preferably 1545-1555 ℃, more preferably 1550 ℃; the heat preservation time of the second heat preservation is preferably 18-22 min, more preferably 20min; the temperature of the third heat preservation is preferably 1595-1605 ℃, more preferably 1600 ℃; the heat preservation time of the third heat preservation is preferably 28-32 min, more preferably 30min. The invention sets the heat preservation temperature and time in the refining process to be in the above range, so that Se, te, bi, pb, cu and other impurity elements in the alloy melt can be better removed.
In the present invention, the temperature rising rate of the first temperature rising is not particularly limited, and the first temperature rising rate commonly used by those skilled in the art may be adopted to raise the temperature to the first heat-preserving temperature.
In the invention, the heating rate of the second heating is preferably 4-6 ℃/min, more preferably 5 ℃/min; the heating rate of the third heating is preferably 2-3 ℃/min, more preferably 2.5 ℃/min. The invention limits the temperature rising rate of the second temperature rising and the third temperature rising to the above range, which can fully ensure the removal of impurity elements in the master alloy.
In the invention, the refining also comprises cooling treatment of the alloy melt after heat preservation.
In the present invention, the cooling treatment is preferably power failure cooling.
In the present invention, the temperature of the refined product is preferably 1470 to 1490 ℃, more preferably 1480 ℃. The invention limits the temperature of the refined product to the above range, which is beneficial to smelting the subsequent raw materials.
The present invention preferably agitates the alloy melt after adding aluminum, residual carbon, hafnium and nickel boron master alloy.
In the present invention, the stirring power is preferably 120kW, and the stirring time is preferably 10min. The invention can make the alloy components more uniform by stirring.
After alloy melt is obtained, a desulfurizing agent, yttrium, nickel lanthanum intermediate alloy and nickel cerium intermediate alloy are sequentially added into the alloy melt in an argon atmosphere, deoxidization and desulfurization are carried out, and casting is carried out, so that the high-temperature alloy for the turbine blade of the gas turbine is obtained.
In the present invention, the pressure of argon in the argon atmosphere is preferably 1900 to 2100Pa, more preferably 2000Pa. The present invention can improve the purity of the alloy by limiting the pressure of argon gas to the above range.
The type of the desulfurizing agent is not particularly limited, and a desulfurizing agent commonly used by those skilled in the art may be used.
In the invention, the purity of the yttrium is preferably not lower than Y99.99; the brand HB-Z131-2020 high-temperature alloy master alloy adopts the brand specified in the technical requirement of raw materials. The purity of yttrium is limited to the above range, and the purity of the alloy can be improved.
In the present invention, the nickel-lanthanum master alloy is preferably a nickel-lanthanum master alloy having a lanthanum content of 10 wt%.
In the present invention, the nickel-cerium intermediate alloy is preferably a nickel-cerium intermediate alloy having a cerium content of 65 wt%.
The invention preferably stirs the alloy melt after adding desulfurizing agent, yttrium, nickel lanthanum intermediate alloy and nickel cerium intermediate alloy.
In the present invention, the stirring power is preferably 80kW, and the stirring time is preferably 5min. The invention can make the alloy components more uniform by stirring.
In the invention, the temperature of the deoxidation and desulfurization is preferably 1515-1525 ℃, more preferably 1520 ℃; the temperature keeping time of deoxidation and desulfurization is preferably 3-5 min. The invention limits the temperature and time of deoxidation and desulfurization to the above range, so that the O and S contents in the alloy can be reduced.
In the invention, the pouring power is preferably 45-55 kW, more preferably 50kW. The present invention can obtain an alloy of better quality by limiting the pouring power to the above range.
The invention is regulated by controlling the feeding and smelting processes of raw materials, specifically, part of carbon is added in the slow melting period to react with oxygen remained in the furnace and on the surface of metal in the early slow melting process, oxygen atoms are removed, aluminum is added after refining to avoid the influence of thermite reaction on smelting, yttrium, nickel-cerium intermediate alloy and nickel-lanthanum intermediate alloy are added in the deoxidizing and desulfurizing period, the large deviation of volatile yttrium, cerium and lanthanum in the smelting process can be avoided, and meanwhile, the alloy melt can be purified.
The invention also provides application of the high-temperature alloy for the gas turbine blade or the high-temperature alloy for the gas turbine blade prepared by the preparation method in the technical scheme in the gas turbine blade with the use temperature of more than 1000 ℃.
The technical solutions of the present invention will be clearly and completely described in the following in connection with the embodiments of the present invention. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
The high-temperature alloy for the turbine blade of the gas turbine consists of the following element components in percentage by mass: carbon 0.03%, rhenium 2.5%, molybdenum 1%, aluminum 7%, tantalum 7%, chromium 8.5%, cobalt 9%, tungsten 4.5%, boron 0.003%, hafnium 0.12%, yttrium 0.0007%, lanthanum 0.0003%, impurity elements: h0.00005%, O0.0005%, N0.0003%, S0.0006%, zn < 0.0005%, ga 0.00006%, ge < 0.0001%, as 0.0002%, br < 0.00001%, rb < 0.00001%, sr < 0.0005%, ru 0.00005%, rh < 0.00001%, cd < 0.00001%, in 0.000006%, sn < 0.00005%, sb < 0.00005%, ca 0.00005%, cs < 0.00001%, ba 0.00008%, bi < 0.00001%, pr < 0.00001%, ho < 0.00001%, er < 0.00001%, tm < 0.00001%, lu < 0.00001%, os < 0.00001%, ir < 0.00001%, au < 0.00001%, hg < 0.00001%, th < 0.00005%, I < 0.00001%, cl < 0.00005%, nd < 0.00001%, U < 0.00001%, K < 0.00001%, pd < 0.00001%, and Ni < 0.00001%, the balance being less than 0.0001% and Ni < 0.0001%;
the preparation method of the high-temperature alloy for the turbine blade of the gas turbine comprises the following steps:
(1) Coating the surface of the spinel crucible with a layer of ZrO 2 Coating and fully sintering, polishing oxide skin by adopting a roller before feeding alloy raw materials, ultrasonically cleaning by using absolute ethyl alcohol, and drying for later use; the sintering process is that after the temperature is kept at 600 ℃ for 2 hours, the temperature is raised to 900 ℃ at the temperature rising rate of 5 ℃/min for 2 hours, and then the temperature is raised to 1200 ℃ at the temperature rising rate of 5 ℃/min for 2 hours;
(2) Sequentially charging electrolytic nickel (Ni 9996), metallic cobalt (Co 9995), molybdenum strip (Mo-1), partial carbon (spectral graphite electrode (TSG)), tantalum strip (TD-T), metallic tungsten (TW-1), rhenium (Re 99.99), metallic chromium (GCCr-1) and residual nickel, and vacuumizing to a vacuum degree of less than 10 -1 After Pa, power transmission is melted, the power transmission power is increased stepwise, and the initial state is thatThe initial power supply is 80kW, the power is increased to 150kW after the alloy turns red, the power is increased to 180kW for refining after the alloy is completely melted, the temperature of the alloy melt is increased to 1500 ℃, the temperature is kept for 10min, the temperature is increased to 1550 ℃ at the heating rate of 5 ℃/min, the temperature is kept for 20min, the temperature is increased to 1600 ℃ at 2.5 ℃/min, the temperature is kept for 30min, finally the power is cut off, the temperature is reduced to 1480 ℃, and after refining, remelting refined aluminum ingot (Al99.99), residual carbon, hafnium sponge (HHf-01) and nickel-boron intermediate alloy with the boron content of 20wt% are sequentially added, and the alloy melt is obtained by stirring for 10min with 120 kW;
(3) And (3) filling argon into the alloy melt, adding a desulfurizing agent, metal yttrium (Y99.99), nickel-lanthanum intermediate alloy with the lanthanum content of 10wt% and nickel-cerium intermediate alloy with the cerium content of 65wt% into the alloy melt after the argon pressure reaches 2000Pa, stirring for 5min, refining for 3-5 min at 1520 ℃ after stirring, deoxidizing and desulfurizing, and pouring with the pouring power of 50kW to obtain the high-temperature alloy for the turbine blade of the gas turbine.
Example 2
The high-temperature alloy for the turbine blade of the gas turbine consists of the following element components in percentage by mass: 0.05% of carbon, 2.9% of rhenium, 0.3% of molybdenum, 6% of aluminum, 5% of tantalum, 8% of chromium, 8.5% of cobalt, 4.5% of tungsten, 0.005% of boron, 0.17% of hafnium, 0.004% of yttrium, 0.006% of lanthanum, 0.004% of cerium, and impurity elements: h0.00008%, O0.0004%, N0.00009%, S0.0006%, zn < 0.0005%, ga 0.00006%, ge < 0.0001%, as 0.0002%, br < 0.00001%, rb < 0.00001%, sr < 0.0005%, ru 0.00005%, rh < 0.00001%, cd < 0.00001%, in 0.000009%, sn < 0.00005%, sb < 0.00005%, ca 0.00005%, cs < 0.00001%, ba 0.0001%, bi < 0.00001%, pr < 0.00001%, ho < 0.00001%, er < 0.00001%, tm < 0.00001%, lu < 0.00001%, os < 0.00001%, ir < 0.00001%, au < 0.00001%, hg < 0.00001%, th < 0.00005%, I < 0.00001%, cl < 0.00005%, nd < 0.00001%, U < 0.00005%, K < 0.0001%, pd < 0.00001%, and Ni < 0.0003% for the balance of Ni and Ni < 0.0001%;
the method for preparing the superalloy for a gas turbine blade is the same as in example 1.
Comparative example 1
The high-temperature alloy for the turbine blade of the gas turbine consists of the following element components in percentage by mass: 0.05% of carbon, 2.8% of rhenium, 1.4% of molybdenum, 6.2% of aluminum, 6.5% of tantalum, 7% of chromium, 7.5% of cobalt, 5% of tungsten, 0.004% of boron, 0.15% of hafnium and impurity elements: h0.00005%, O0.0006%, N0.0001%, S0.0005%, zn < 0.0005%, ga 0.00006%, ge < 0.0001%, as 0.0002%, br < 0.00001%, rb < 0.00001%, sr < 0.0005%, ru 0.00005%, rh < 0.00001%, cd < 0.00001%, in 0.000005%, sn < 0.00005%, sb < 0.00005%, ca 0.00005%, cs < 0.00001%, ba 0.00008%, bi < 0.00001%, pr < 0.00001%, ho < 0.00001%, er < 0.00001%, tm < 0.00001%, lu < 0.00001%, os < 0.00001%, ir < 0.00001%, au < 0.00001%, hg < 0.00001%, th < 0.00005%, I < 0.00001%, cl < 0.00005%, nd < 0.00001%, U < 0.00005%, K < 0.00001%, pd < 0.00001%, and Ni < 0.00001%, the balance being less than 0.0003%;
the method for preparing the superalloy for a gas turbine blade is the same as in example 1.
The high-temperature alloy for the turbine blade of the gas turbine prepared in examples 1-2 and comparative example 1 is tested for oxidation resistance, hot corrosion performance, high-temperature tensile performance, high-temperature durability performance and high-cycle fatigue performance, and the specific test method is as follows:
oxidation resistance: detection is carried out according to HB5258 'test method for measuring the oxidation resistance of steel and superalloy';
hot corrosion performance: detecting according to HB7740, gas hot corrosion test method;
high temperature tensile properties: detection is carried out according to HB5195 metal high temperature tensile test method;
high temperature durability: detection is carried out according to HB5150 'method for high temperature endurance test of metals';
high cycle fatigue performance: the detection is carried out according to HB 20449-2018 'high-temperature axial high-cycle fatigue test method of metallic materials'.
The oxidation resistance, the structural stability and the hot corrosion performance of the superalloy for gas turbine blades prepared in examples 1 to 2 and comparative example 1 are shown in Table 1:
TABLE 1 high temperature alloys for gas turbine blades prepared in examples 1-2 and comparative example 1 have oxidation resistance, tissue stability and hot corrosion resistance
The high-temperature tensile properties of the high-temperature alloy for gas turbine blades prepared in examples 1 to 2 and comparative example 1 are shown in tables 2 to 4:
TABLE 2 high temperature tensile Property of high temperature alloys for gas turbine blades prepared in example 1
TABLE 3 high temperature tensile Property of high temperature alloys for gas turbine blades prepared in example 2
Table 4 high temperature tensile properties of the high temperature alloy for gas turbine blades prepared in comparative example 1
Examples the high temperature durability properties of the high temperature alloys for gas turbine blades prepared in examples 1 to 2 and comparative example 1 are shown in tables 5 to 7:
TABLE 5 high temperature durability properties of high temperature alloys for gas turbine blades prepared in example 1
TABLE 6 high temperature durability properties of high temperature alloys for gas turbine blades prepared in example 2
Table 7 high temperature durability properties of the high temperature alloys for gas turbine blades prepared in comparative example 1
The high cycle fatigue properties at 1120℃of the high temperature alloys for gas turbine blades prepared in examples 1 to 2 and comparative example 1 are shown in Table 8:
table 8 high cycle fatigue properties at 1120℃of the superalloy for gas turbine blades prepared in examples 1 to 2 and comparative example 1
As is evident from the high-temperature alloys for gas turbine blades prepared in examples 1 to 2 and comparative example 1 in tables 1 to 8, the high-temperature alloys for gas turbine blades prepared by the method of the present invention are completely resistant to oxidation at 1100℃at oxidation rates of 0.03 to 0.04 g/m 2 H, the high-temperature structure stability at 1000 ℃ for 2000h is good, no TCP phase is separated out, and the hot corrosion rate is 0.04-0.05 g/(m) 2 H), high temperature tensile Strength delta at 1100 DEG C b 400-420 MPa, yield strength delta p0.2 235-265 MPa, the breaking time of high-temperature durability performance at 1100 ℃ under 158MPa is 38-45 h, and the high-cycle fatigue performance at 1120 ℃ under the maximum stress delta max Fracture cycle N at 70MPa f Is (9-10) x 10 6 Has high strength and good corrosion resistance and oxidation resistance, can be applied to the turbine blade of the gas turbine with the service temperature of more than 1000 ℃.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention.
Claims (10)
1. A superalloy for a gas turbine blade, comprising, in mass percent: 0.001-0.1% of carbon, 1-2.9% of rhenium, 0.2-1.5% of molybdenum, 6-8% of aluminum, 3-7% of tantalum, 6-10% of chromium, 6-10% of cobalt, 3-5% of tungsten, 0.003-0.006% of boron, 0.1-0.2% of hafnium, 0.001% or more of yttrium+lanthanum and 0.01% or less, 0.005% or less of cerium, 0.04% or less of impurity elements and the balance of nickel.
2. The superalloy for a gas turbine blade according to claim 1, wherein the impurity elements comprise one or more of H, O, N, S, zn, ga, ge, as, br, rb, sr, ru, rh, cd, in, sn, sb, ca, cs, ba, bi, pr, ho, er, tm, lu, os, ir, au, hg, th, I, cl, nd, U, K, yb, li, pt and Pd;
the content of H is less than or equal to 1ppm;
the content of O, N and S is independently less than or equal to 6ppm;
the mass content of Zn, ga, ge, as, br, rb, sr, ru, rh, cd, in, sn, sb, ca, cs, ba, bi, pr, ho, er, tm, lu, os, ir, au, hg, th, I, cl, nd, U, K, yb, li, pt and Pd is independently less than or equal to 0.002 percent.
3. A method of preparing the superalloy for a gas turbine blade as claimed in claim 1 or claim 2, comprising the steps of:
feeding according to the sequence of partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, rhenium, chromium and residual nickel, sequentially melting and refining, and sequentially adding aluminum, residual carbon, hafnium and nickel-boron intermediate alloy to obtain alloy melt;
and in the argon atmosphere, sequentially adding a desulfurizing agent, yttrium, nickel-lanthanum intermediate alloy and nickel-cerium intermediate alloy into the alloy melt, deoxidizing and desulfurizing, and then pouring to obtain the high-temperature alloy for the turbine blade of the gas turbine.
4. A method of preparing according to claim 3, wherein the melting and refining are both performed under vacuum;
the vacuum degree of the vacuum is less than 10 -1 Pa。
5. The production method according to claim 3 or 4, wherein the refining includes a first heat preservation after a first temperature rise, a second heat preservation after a second temperature rise, and a third heat preservation after a third temperature rise, which are sequentially performed;
the temperature of the first heat preservation is 1490-1510 ℃, and the heat preservation time is 9-11 min;
the temperature of the second heat preservation is 1545-1555 ℃, and the heat preservation time is 18-22 min;
the temperature of the third heat preservation is 1595-1605 ℃, and the heat preservation time is 28-32 min.
6. The preparation method according to claim 5, wherein the second temperature rise rate is 4-6 ℃/min;
and the temperature rising rate of the third temperature rising is 2-3 ℃/min.
7. The method according to claim 6, wherein the temperature of the refined product is 1470 to 1490 ℃.
8. The method according to claim 3, wherein the pressure of argon in the argon atmosphere is 1900-2100 Pa.
9. The method according to claim 3, wherein the deoxidizing and desulfurizing temperature is 1515-1525 ℃ and the heat-preserving time is 3-5 min.
10. Use of the superalloy for a gas turbine blade according to claim 1 or 2 or the superalloy for a gas turbine blade according to any of the preparation methods according to claims 3 to 9 in a gas turbine blade having a service temperature of 1000 ℃ or higher.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0194391A1 (en) * | 1985-03-13 | 1986-09-17 | General Electric Company | Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys |
| US20010001968A1 (en) * | 1998-02-20 | 2001-05-31 | Hiroyuki Kawaura | Method of producing a metallic part exhibiting excellent oxidation resistance |
| CN107034387A (en) * | 2016-02-04 | 2017-08-11 | 中国科学院金属研究所 | A kind of low segregation nickel-base high-temperature single crystal alloy of high-strength corrosion and heat resistant |
| CN111364096A (en) * | 2020-03-30 | 2020-07-03 | 上海交通大学 | Substrate-triggered single crystal high-temperature alloy directional solidification process |
| CN112226648A (en) * | 2020-09-08 | 2021-01-15 | 中国科学院金属研究所 | Low-Re low-S heat-corrosion-resistant nickel-based single crystal superalloy |
| CN113215513A (en) * | 2021-05-11 | 2021-08-06 | 成都中科翼能科技有限公司 | Novel post-treatment process for abradable Al/BN sealing coating of gas turbine part |
| US20220062992A1 (en) * | 2020-08-30 | 2022-03-03 | Central South University | Nickel-based superalloy for 3d printing and powder preparation method thereof |
| CN114959326A (en) * | 2022-03-28 | 2022-08-30 | 江苏美特林科特殊合金股份有限公司 | Purifying smelting method of K640S cobalt-based high-temperature alloy |
| CN115433844A (en) * | 2022-08-16 | 2022-12-06 | 中国科学院金属研究所 | Preparation method of ultralow-sulfur high-temperature alloy based on efficient solid-liquid reaction of oxide and melt |
-
2024
- 2024-02-04 CN CN202410153036.7A patent/CN117684047B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0194391A1 (en) * | 1985-03-13 | 1986-09-17 | General Electric Company | Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys |
| US20010001968A1 (en) * | 1998-02-20 | 2001-05-31 | Hiroyuki Kawaura | Method of producing a metallic part exhibiting excellent oxidation resistance |
| CN107034387A (en) * | 2016-02-04 | 2017-08-11 | 中国科学院金属研究所 | A kind of low segregation nickel-base high-temperature single crystal alloy of high-strength corrosion and heat resistant |
| CN111364096A (en) * | 2020-03-30 | 2020-07-03 | 上海交通大学 | Substrate-triggered single crystal high-temperature alloy directional solidification process |
| US20220062992A1 (en) * | 2020-08-30 | 2022-03-03 | Central South University | Nickel-based superalloy for 3d printing and powder preparation method thereof |
| CN112226648A (en) * | 2020-09-08 | 2021-01-15 | 中国科学院金属研究所 | Low-Re low-S heat-corrosion-resistant nickel-based single crystal superalloy |
| CN113215513A (en) * | 2021-05-11 | 2021-08-06 | 成都中科翼能科技有限公司 | Novel post-treatment process for abradable Al/BN sealing coating of gas turbine part |
| CN114959326A (en) * | 2022-03-28 | 2022-08-30 | 江苏美特林科特殊合金股份有限公司 | Purifying smelting method of K640S cobalt-based high-temperature alloy |
| CN115433844A (en) * | 2022-08-16 | 2022-12-06 | 中国科学院金属研究所 | Preparation method of ultralow-sulfur high-temperature alloy based on efficient solid-liquid reaction of oxide and melt |
Non-Patent Citations (1)
| Title |
|---|
| 尚根峰等: "Y-La添加对镍基单晶高温合金界面反应及循环氧化行为的影响", 航空材料学报, vol. 38, no. 6, 30 November 2018 (2018-11-30), pages 43 - 49 * |
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