CN117660810B - High-purity high-temperature master alloy for variable-cycle gas engine turbine blade and preparation method and application thereof - Google Patents
High-purity high-temperature master alloy for variable-cycle gas engine turbine blade and preparation method and application thereof Download PDFInfo
- Publication number
- CN117660810B CN117660810B CN202410130629.1A CN202410130629A CN117660810B CN 117660810 B CN117660810 B CN 117660810B CN 202410130629 A CN202410130629 A CN 202410130629A CN 117660810 B CN117660810 B CN 117660810B
- Authority
- CN
- China
- Prior art keywords
- temperature
- alloy
- heat preservation
- gas engine
- cycle gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000956 alloy Substances 0.000 title claims abstract description 203
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 201
- 238000002360 preparation method Methods 0.000 title claims abstract description 15
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 45
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 35
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 33
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 28
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims abstract description 27
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 26
- 239000011651 chromium Substances 0.000 claims abstract description 24
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 23
- 229910052715 tantalum Inorganic materials 0.000 claims abstract description 23
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 23
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 22
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 22
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 22
- 239000010941 cobalt Substances 0.000 claims abstract description 22
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 22
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 22
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims abstract description 22
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 21
- 239000010937 tungsten Substances 0.000 claims abstract description 21
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 20
- 239000011733 molybdenum Substances 0.000 claims abstract description 20
- 239000012535 impurity Substances 0.000 claims abstract description 19
- 229910052746 lanthanum Inorganic materials 0.000 claims abstract description 19
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910052684 Cerium Inorganic materials 0.000 claims abstract description 18
- GWXLDORMOJMVQZ-UHFFFAOYSA-N cerium Chemical compound [Ce] GWXLDORMOJMVQZ-UHFFFAOYSA-N 0.000 claims abstract description 17
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229910052796 boron Inorganic materials 0.000 claims abstract description 14
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 12
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 11
- 239000010936 titanium Substances 0.000 claims abstract description 11
- 239000007789 gas Substances 0.000 claims description 71
- 238000004321 preservation Methods 0.000 claims description 44
- 238000000034 method Methods 0.000 claims description 22
- 238000007670 refining Methods 0.000 claims description 20
- 230000003009 desulfurizing effect Effects 0.000 claims description 16
- 230000000630 rising effect Effects 0.000 claims description 15
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 12
- 229910052760 oxygen Inorganic materials 0.000 claims description 12
- 238000002844 melting Methods 0.000 claims description 11
- 230000008018 melting Effects 0.000 claims description 11
- WITQLILIVJASEQ-UHFFFAOYSA-N cerium nickel Chemical compound [Ni].[Ce] WITQLILIVJASEQ-UHFFFAOYSA-N 0.000 claims description 10
- DOARWPHSJVUWFT-UHFFFAOYSA-N lanthanum nickel Chemical compound [Ni].[La] DOARWPHSJVUWFT-UHFFFAOYSA-N 0.000 claims description 10
- 229910052717 sulfur Inorganic materials 0.000 claims description 10
- 229910052691 Erbium Inorganic materials 0.000 claims description 9
- 229910052689 Holmium Inorganic materials 0.000 claims description 9
- 229910052765 Lutetium Inorganic materials 0.000 claims description 9
- 229910052779 Neodymium Inorganic materials 0.000 claims description 9
- 229910052777 Praseodymium Inorganic materials 0.000 claims description 9
- 229910052776 Thorium Inorganic materials 0.000 claims description 9
- 229910052775 Thulium Inorganic materials 0.000 claims description 9
- 229910052770 Uranium Inorganic materials 0.000 claims description 9
- 229910052769 Ytterbium Inorganic materials 0.000 claims description 9
- 229910052787 antimony Inorganic materials 0.000 claims description 9
- 229910052785 arsenic Inorganic materials 0.000 claims description 9
- 229910052797 bismuth Inorganic materials 0.000 claims description 9
- QDWJUBJKEHXSMT-UHFFFAOYSA-N boranylidynenickel Chemical compound [Ni]#B QDWJUBJKEHXSMT-UHFFFAOYSA-N 0.000 claims description 9
- 229910052793 cadmium Inorganic materials 0.000 claims description 9
- 229910052792 caesium Inorganic materials 0.000 claims description 9
- 239000003795 chemical substances by application Substances 0.000 claims description 9
- 229910052733 gallium Inorganic materials 0.000 claims description 9
- 229910052732 germanium Inorganic materials 0.000 claims description 9
- 229910052737 gold Inorganic materials 0.000 claims description 9
- 229910052738 indium Inorganic materials 0.000 claims description 9
- 229910052741 iridium Inorganic materials 0.000 claims description 9
- 229910052744 lithium Inorganic materials 0.000 claims description 9
- 229910052753 mercury Inorganic materials 0.000 claims description 9
- 229910052757 nitrogen Inorganic materials 0.000 claims description 9
- 229910052762 osmium Inorganic materials 0.000 claims description 9
- 229910052697 platinum Inorganic materials 0.000 claims description 9
- 229910052700 potassium Inorganic materials 0.000 claims description 9
- 229910052703 rhodium Inorganic materials 0.000 claims description 9
- 229910052701 rubidium Inorganic materials 0.000 claims description 9
- 229910052707 ruthenium Inorganic materials 0.000 claims description 9
- 229910052718 tin Inorganic materials 0.000 claims description 9
- 239000012300 argon atmosphere Substances 0.000 claims description 8
- 229910052763 palladium Inorganic materials 0.000 claims description 8
- 238000006477 desulfuration reaction Methods 0.000 claims description 7
- 230000023556 desulfurization Effects 0.000 claims description 7
- 229910052786 argon Inorganic materials 0.000 claims description 6
- 229910052725 zinc Inorganic materials 0.000 claims description 6
- 229910000601 superalloy Inorganic materials 0.000 claims description 2
- 230000003647 oxidation Effects 0.000 abstract description 28
- 238000007254 oxidation reaction Methods 0.000 abstract description 28
- 238000005260 corrosion Methods 0.000 abstract description 17
- 230000007797 corrosion Effects 0.000 abstract description 17
- 229910000990 Ni alloy Inorganic materials 0.000 abstract description 2
- 239000002994 raw material Substances 0.000 description 16
- 230000001276 controlling effect Effects 0.000 description 12
- 210000001787 dendrite Anatomy 0.000 description 12
- 238000003756 stirring Methods 0.000 description 10
- 238000003723 Smelting Methods 0.000 description 9
- 238000010438 heat treatment Methods 0.000 description 9
- 239000000306 component Substances 0.000 description 8
- 238000005728 strengthening Methods 0.000 description 7
- 238000001514 detection method Methods 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 238000005245 sintering Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 5
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 239000006104 solid solution Substances 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000001680 brushing effect Effects 0.000 description 3
- 238000005336 cracking Methods 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010309 melting process Methods 0.000 description 3
- 238000005498 polishing Methods 0.000 description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- -1 meanwhile Substances 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 125000004430 oxygen atom Chemical group O* 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000003595 spectral effect Effects 0.000 description 2
- 229910052596 spinel Inorganic materials 0.000 description 2
- 239000011029 spinel Substances 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 239000003832 thermite Substances 0.000 description 2
- 239000011573 trace mineral Substances 0.000 description 2
- 235000013619 trace mineral Nutrition 0.000 description 2
- 238000004506 ultrasonic cleaning Methods 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000010981 drying operation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009661 fatigue test Methods 0.000 description 1
- 238000011049 filling Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910052711 selenium Inorganic materials 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 238000011895 specific detection Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a high-purity high-temperature master alloy for a variable cycle gas engine turbine blade, and a preparation method and application thereof, and belongs to the technical field of nickel alloy materials. The invention provides a high-purity high-temperature master alloy for a variable cycle gas engine turbine blade, which comprises the following element components in percentage by mass: 0.001-0.1% of carbon, 10-15% of chromium, 8.5-9.5% of cobalt, 2-3.8% of tungsten, 0.5-1.5% of molybdenum, 2-3.3% of aluminum, 3.5-5% of titanium, 2-3% of tantalum, 0-0.01% of boron, less than or equal to 0.01% of yttrium and lanthanum, less than or equal to 0.005% of cerium, less than or equal to 0.04% of impurity elements and the balance of nickel. The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade has high strength and good corrosion resistance and oxidation resistance, and can be applied to the variable cycle gas engine turbine blade with the use temperature below 1000 ℃.
Description
Technical Field
The invention relates to the technical field of nickel alloy materials, in particular to a high-purity high-temperature master alloy for a turbine blade of a variable cycle gas engine, and a preparation method and application thereof.
Background
With the development of ship technology, the development of ship power is in great demand. At present, the national gas turbine is the primary choice of ship power, the thermodynamic cycle characteristic of the traditional gas turbine is fixed, and the engine can only work in one mode. The characteristic of ship power requires that the engine be in different working states under different conditions, so that for the core component of the gas turbine, the turbine rotor is often in complex environments such as cold-hot alternation, stress alternation and the like, which is a great challenge for the materials of the turbine blades.
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, developing a high-purity high-temperature master alloy for a turbine blade of a variable cycle gas engine with long service life, corrosion resistance, oxidation resistance and high strength is a technical problem to be solved urgently in the field.
Disclosure of Invention
The invention aims to provide a high-purity high-temperature master alloy for a variable cycle gas engine turbine blade, and a preparation method and application thereof.
In order to achieve the above object, the present invention provides the following technical solutions:
The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade is characterized by comprising the following element components in percentage by mass: 0.001-0.1% of carbon, 10-15% of chromium, 8.5-9.5% of cobalt, 2-3.8% of tungsten, 0.5-1.5% of molybdenum, 2-3.3% of aluminum, 3.5-5% of titanium, 2-3% of tantalum, 0-0.01% of boron, less than or equal to 0.01% of yttrium and lanthanum, less than or equal to 0.005% of cerium, less than or equal to 0.04% 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade, which comprises the following steps:
Feeding according to the sequence of partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, chromium and residual nickel, sequentially melting and refining, and sequentially adding aluminum, residual carbon 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade.
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-purity high-temperature master alloy for the variable cycle gas engine turbine blade or the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade prepared by the preparation method in the technical scheme in the variable cycle gas engine turbine blade with the use temperature below 1000 ℃.
The invention provides a high-purity high-temperature master alloy for a variable cycle gas engine turbine blade, which comprises the following element components in percentage by mass: 0.001-0.1% of carbon, 10-15% of chromium, 8.5-9.5% of cobalt, 2-3.8% of tungsten, 0.5-1.5% of molybdenum, 2-3.3% of aluminum, 3.5-5% of titanium, 2-3% of tantalum, 0-0.01% of boron, less than or equal to 0.01% of yttrium and lanthanum, less than or equal to 0.005% of cerium, less than or equal to 0.04% of impurity elements and the balance of nickel. According to the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade, chromium exists in a matrix in a solid solution state by adding chromium element, 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, titanium 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; 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; by reducing the content of impurity elements, the performance of the alloy is further improved. The results of the examples show that the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade provided by the invention has complete oxidation resistance at 900 ℃, the oxidation rate is 0.08-0.095 g/m 2 h, the high-temperature tissue stability at 900 ℃ for 2000h is good, no TCP phase is separated out, the hot corrosion rate is 0.14-0.18 g/(m 2 h), the high-temperature tensile strength delta b at 1000 ℃ is 320-356 MPa, the yield strength delta p0.2 is 220-260 MPa, the fracture time of the high-temperature durability performance at 1000 ℃ is 560-586 h when the stress delta is 135MPa, the fracture cycle N f＞1×107 when the high-cycle fatigue performance at 900 ℃ is 450MPa when the maximum stress delta max is 2500 weeks, and the variable cycle gas engine turbine blade has no crack, 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, cerium and lanthanum 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-purity high-temperature master alloy for a variable cycle gas engine turbine blade, which comprises the following element components in percentage by mass: 0.001-0.1% of carbon, 10-15% of chromium, 8.5-9.5% of cobalt, 2-3.8% of tungsten, 0.5-1.5% of molybdenum, 2-3.3% of aluminum, 3.5-5% of titanium, 2-3% of tantalum, 0-0.01% of boron, less than or equal to 0.01% of yttrium and lanthanum, less than or equal to 0.005% of cerium and the balance nickel.
The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises, by mass, 10-15% of chromium, preferably 12.5-14%, and more preferably 13.5%. 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises 8.5-9.5% of cobalt, preferably 8.7-9.3% of cobalt, and more preferably 9% of cobalt. 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises 2-3.8% of tungsten, preferably 2.4-3.4% of tungsten, and more preferably 3.4% 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises 0.5-1.5% of molybdenum, preferably 0.8-1% 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises 2-3.3% of aluminum, preferably 2.5-3% 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises 3.5-5% of titanium, preferably 3.75-4.9%, and more preferably 4-4.5% of titanium. In the present invention, by controlling the content of titanium 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises 2-3% of tantalum, preferably 2.2-2.8%, and more preferably 2.5% 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises 0-0.01% of boron, preferably 0.004-0.008%, and more preferably 0.006% of boron by mass percent. 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises less than or equal to 0.01% of yttrium and lanthanum, and preferably 0.003-0.007% of yttrium and lanthanum in percentage by mass. 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises less than or equal to 0.005% of cerium, and preferably 0.002-0.004% 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade 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 6ppm or less; 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade 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 tissue 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 impurity element content 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade, which comprises the following steps:
Feeding according to the sequence of partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, chromium and residual nickel, sequentially melting and refining, and sequentially adding aluminum, residual carbon 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade.
According to the method, partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, chromium and residual nickel are sequentially fed, melted and refined, and then aluminum, residual carbon 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 present invention limits the purity of nickel to the above-described range, and can improve the purity of the master alloy.
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 master 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 master 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 master 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 master 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 present invention limits the purity of tungsten to the above range, and can improve the purity of the master alloy.
In the invention, the purity of the chromium is preferably grade no 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 master 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 present invention can improve the purity of the master alloy by limiting the purity of aluminum 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 carries out sintering treatment after brushing a ZrO 2 coating on the surface of the crucible before feeding.
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 invention, the thickness of the ZrO 2 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. According to the invention, the temperature resistance of the crucible can be increased by brushing a layer of ZrO 2 coating on the surface 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 both 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 master 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 master alloy by setting the electric power to be in the above range, allowing the alloy to be melted more easily, and removing the O impurity from 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 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade 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 master 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 master 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 a master 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade or the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade prepared by the preparation method in the technical scheme in the variable cycle gas engine turbine blade with the use temperature below 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-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises the following element components in percentage by mass: 0.03% of carbon, 14% of chromium, 9.5% of cobalt, 3.8% of tungsten, 1.5% of molybdenum, 3.3% of aluminum, 4.9% of titanium, 2.8% of tantalum, 0.01% of boron, 0.004% of yttrium, 0.001% of lanthanum, 0.002% of cerium, 0.0003% of impurity elements ：H 0.00005%、O 0.0005%、N 0.0003%、S 0.0006%、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＜0.00005%、K＜0.0001%、Yb＜0.00001%、Li＜0.00001%、Pt＜0.0001% and Pd, and the balance of nickel;
the preparation method of the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises the following steps of:
(1) Brushing a layer of ZrO 2 coating on the surface of the spinel crucible, fully sintering, polishing oxide skin by adopting a roller before feeding the 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), metallic chromium (GCCr-1) and residual nickel, vacuumizing, feeding power after the vacuum degree is lower than 10 -1 Pa for melting, feeding power for step increase, initial feeding power is 80kW, adding the power to 150kW after the alloy turns red, adding the power to 180kW for refining after the alloy is completely melted, heating the alloy solution to 1500 ℃ for 10min, heating to 1550 ℃ at a heating rate of 5 ℃/min, heating to 20min, heating to 1600 ℃ for 30min at 2.5 ℃/min, finally cooling to 1480 ℃ after power failure, sequentially adding a remelting refined aluminum ingot (Al99.99), and a nickel-boron intermediate alloy with the residual carbon and boron content of 20wt% after refining, and stirring for 10min at 120kW to obtain the alloy solution;
(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-purity master alloy for the turbine blade of the variable cycle gas engine.
Example 2
The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises the following element components in percentage by mass: 0.05% of carbon, 12.5% of chromium, 9% of cobalt, 3% of tungsten, 1% of molybdenum, 2.6% of aluminum, 3.75% of titanium, 2.5% of tantalum, 0.005% of boron, 0.007% of yttrium, 0.003% of lanthanum, 0.004% of cerium, 0.0003% of impurity elements ：H 0.00008%、O 0.0004%、N 0.00009%、S 0.0006%、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%、Yb＜0.00001%、Li＜0.00001%、Pt＜0.0001% and Pd, and the balance of nickel;
The preparation method of the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade is the same as that of the embodiment 1.
Example 3
The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises the following element components in percentage by mass: 0.05% of carbon, 10% of chromium, 8.7% of cobalt, 2.4% of tungsten, 0.8% of molybdenum, 2.5% of aluminum, 3.5% of titanium, 2.2% of tantalum, 0.004% of boron, ：H 0.00005%、O 0.0006%、N 0.0001%、S 0.0005%、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＜0.0001%、Yb＜0.00001%、Li＜0.00001%、Pt＜0.0001%% of impurity elements and 0.0003% of Pd, and the balance of nickel;
The preparation method of the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade is the same as that of the embodiment 1.
The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade prepared in the embodiment 1-3 is subjected to detection of oxidation resistance, hot corrosion performance, high-temperature tensile performance, high-temperature durability performance, high-cycle fatigue performance and cold-hot fatigue performance, and the specific detection 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: detection is carried out according to HB 20449-2018 'high-temperature axial high-cycle fatigue test method of metallic materials';
cold and hot fatigue performance: the detection is carried out according to HB 6660-2011 'method for testing thermal fatigue of sheet Metal'.
The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade prepared in examples 1 to 3 is shown in table 1:
table 1 high purity high temperature master alloy for turbine blade of variable cycle gas engine prepared in examples 1 to 3 has oxidation resistance, structural stability, hot corrosion performance and cold and hot fatigue performance
The high-temperature tensile properties of the high-purity high-temperature master alloy for variable cycle gas engine turbine blades prepared in examples 1 to 3 are shown in tables 2 to 4:
table 2 high temperature tensile properties of high purity high temperature master alloys for variable cycle gas engine turbine blades prepared in example 1
Table 3 high temperature tensile properties of high purity high temperature master alloys for variable cycle gas engine turbine blades prepared in example 2
Table 4 high temperature tensile properties of high purity high temperature master alloys for variable cycle gas engine turbine blades prepared in example 3
The high-temperature durability of the high-purity high-temperature master alloy for variable cycle gas engine turbine blades prepared in examples 1 to 3 is shown in tables 5 to 7:
TABLE 5 high temperature durability properties of high purity high temperature master alloys for variable cycle gas engine turbine blades prepared in EXAMPLE 1
Table 6 high temperature durability properties of high purity high temperature master alloys for variable cycle gas engine turbine blades prepared in example 2
TABLE 7 high temperature durability properties of high purity high temperature master alloys for variable cycle gas engine turbine blades prepared in example 3
The high cycle fatigue properties at 900 ℃ of the high-purity high-temperature master alloy for variable cycle gas engine turbine blades prepared in examples 1 to 3 are shown in Table 8:
Table 8 high cycle fatigue properties at 900 ℃ of high purity high temperature master alloys for variable cycle gas engine turbine blades prepared in examples 1 to 3
As apparent from the properties of the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade prepared in examples 1-3 in tables 1-8, the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade prepared by the method disclosed by the invention has the advantages of complete oxidation resistance at 900 ℃, oxidation rate of 0.08-0.095 g/m 2 h, high-temperature tissue stability at 900 ℃ for 2000h, no TCP phase precipitation, thermal corrosion rate of 0.14-0.18 g/(m 2 h), high-temperature tensile strength delta b at 1000 ℃ of 320-356 MPa, yield strength delta p 0.2 of 220-260 MPa, high-temperature durability at 1000 ℃ of 560-586 h at stress delta of 135MPa, high-cycle fatigue performance at 900 ℃ of N f＞1×107 at maximum stress delta max of 450MPa, no crack occurrence, high strength, good corrosion resistance and oxidation resistance, and can be applied to the variable cycle gas engine turbine blade at the use temperature of below 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 (8)
1. The high-purity high-temperature master alloy for the variable cycle gas engine turbine blade is characterized by comprising the following element components in percentage by mass: 0.001-0.1% of carbon, 10-15% of chromium, 8.5-9.5% of cobalt, 2-3.8% of tungsten, 0.5-1.5% of molybdenum, 2-3.3% of aluminum, 3.5-5% of titanium, 2-3% of tantalum, 0-0.01% of boron, 0.003-0.007% of yttrium+lanthanum, 0.002-0.004% of cerium, less than or equal to 0.04% of impurity elements and the balance of nickel;
The preparation method of the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade comprises the following steps of:
Feeding according to the sequence of partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, chromium and residual nickel, sequentially melting and refining, and sequentially adding aluminum, residual carbon and nickel-boron intermediate alloy to obtain alloy melt;
Sequentially adding a desulfurizing agent, yttrium, nickel-lanthanum intermediate alloy and nickel-cerium intermediate alloy into the alloy melt in an argon atmosphere, deoxidizing and desulfurizing, and then pouring to obtain the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade;
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;
The temperature of deoxidation and desulfurization is 1515-1525 ℃, and the heat preservation time is 3-5 min.
2. The high purity superalloy for a variable cycle gas engine 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 high purity high temperature master alloy for a variable cycle gas engine turbine blade of claim 1 or 2, comprising the steps of:
Feeding according to the sequence of partial nickel, cobalt, molybdenum, partial carbon, tantalum, tungsten, chromium and residual nickel, sequentially melting and refining, and sequentially adding aluminum, residual carbon and nickel-boron intermediate alloy to obtain alloy melt;
Sequentially adding a desulfurizing agent, yttrium, nickel-lanthanum intermediate alloy and nickel-cerium intermediate alloy into the alloy melt in an argon atmosphere, deoxidizing and desulfurizing, and then pouring to obtain the high-purity high-temperature master alloy for the variable cycle gas engine turbine blade;
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;
The temperature of deoxidation and desulfurization is 1515-1525 ℃, and the heat preservation time is 3-5 min.
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 preparation method according to claim 3, wherein the second temperature rise rate is 4-6 ℃/min;
and the temperature rising rate of the third temperature rising is 2-3 ℃/min.
6. The method according to claim 5, wherein the temperature of the refined product is 1470 to 1490 ℃.
7. The method according to claim 3, wherein the pressure of argon in the argon atmosphere is 1900-2100 Pa.
8. The use of the high-purity high-temperature master alloy for variable cycle gas engine turbine blades according to claim 1 or 2 or the high-purity high-temperature master alloy for variable cycle gas engine turbine blades prepared by the preparation method according to any one of claims 3 to 7 in variable cycle gas engine turbine blades with the use temperature below 1000 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410130629.1A CN117660810B (en) | 2024-01-31 | 2024-01-31 | High-purity high-temperature master alloy for variable-cycle gas engine turbine blade and preparation method and application thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410130629.1A CN117660810B (en) | 2024-01-31 | 2024-01-31 | High-purity high-temperature master alloy for variable-cycle gas engine turbine blade and preparation method and application thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117660810A CN117660810A (en) | 2024-03-08 |
| CN117660810B true CN117660810B (en) | 2024-04-16 |
Family
ID=90064463
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410130629.1A Active CN117660810B (en) | 2024-01-31 | 2024-01-31 | High-purity high-temperature master alloy for variable-cycle gas engine turbine blade and preparation method and application thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117660810B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6217286B1 (en) * | 1998-06-26 | 2001-04-17 | General Electric Company | Unidirectionally solidified cast article and method of making |
| US6416596B1 (en) * | 1974-07-17 | 2002-07-09 | The General Electric Company | Cast nickel-base alloy |
| CN1432659A (en) * | 2001-12-18 | 2003-07-30 | 联合工艺公司 | High-strength heat erosion resistant and antioxidant directionally solidified super alloy and its product |
| CN102676880A (en) * | 2011-03-08 | 2012-09-19 | 通用电气公司 | Method of fabricating a component and a component |
| CN103817313A (en) * | 2014-02-24 | 2014-05-28 | 中国科学院金属研究所 | Manufacturing method of one-piece fine-grain centripetal impeller casting |
| CN104894434A (en) * | 2014-03-04 | 2015-09-09 | 中国科学院金属研究所 | Thermal corrosion resistance nickel-based high-temperature alloy having stable structure |
| CN108913922A (en) * | 2018-07-23 | 2018-11-30 | 江苏美特林科特殊合金股份有限公司 | The sublimate method of smelting of Ni-based directional solidification cylindrulite, single crystal super alloy master alloy |
| CN111172430A (en) * | 2018-11-09 | 2020-05-19 | 通用电气公司 | Nickel-based superalloy and article |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100071812A1 (en) * | 2008-09-25 | 2010-03-25 | General Electric Company | Unidirectionally-solidification process and castings formed thereby |
-
2024
- 2024-01-31 CN CN202410130629.1A patent/CN117660810B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6416596B1 (en) * | 1974-07-17 | 2002-07-09 | The General Electric Company | Cast nickel-base alloy |
| US6217286B1 (en) * | 1998-06-26 | 2001-04-17 | General Electric Company | Unidirectionally solidified cast article and method of making |
| CN1432659A (en) * | 2001-12-18 | 2003-07-30 | 联合工艺公司 | High-strength heat erosion resistant and antioxidant directionally solidified super alloy and its product |
| CN102676880A (en) * | 2011-03-08 | 2012-09-19 | 通用电气公司 | Method of fabricating a component and a component |
| CN103817313A (en) * | 2014-02-24 | 2014-05-28 | 中国科学院金属研究所 | Manufacturing method of one-piece fine-grain centripetal impeller casting |
| CN104894434A (en) * | 2014-03-04 | 2015-09-09 | 中国科学院金属研究所 | Thermal corrosion resistance nickel-based high-temperature alloy having stable structure |
| CN108913922A (en) * | 2018-07-23 | 2018-11-30 | 江苏美特林科特殊合金股份有限公司 | The sublimate method of smelting of Ni-based directional solidification cylindrulite, single crystal super alloy master alloy |
| CN111172430A (en) * | 2018-11-09 | 2020-05-19 | 通用电气公司 | Nickel-based superalloy and article |
Non-Patent Citations (6)
| Title |
|---|
| The Effect of Long-Term Thermal Exposure on the Microstructure and Stress Rupture Property of a Directionally Solidified Ni-Based Superalloy;X.W. JIANG、D. WANG等;METALLURGICAL AND MATERIALS TRANSACTIONS A;20141231;第45A卷;6016-6026 * |
| 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;尚根峰、廖金发等;航空材料学报;20180630;第38卷(第6期);43-49 * |
| 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;尚根峰;廖金发;汪航;;航空材料学报;20181130(06);43-49 * |
| 稀土元素对镍基高温合金热强性能的影响及作用;宋燕、阳辉等;中国金属通报;20181231;104-105 * |
| 稀土元素提高耐热合金抗氧化性的机理;王执福, 李河清, 孙本茂, 邢瑞卿, 衣粟, 公志光;铸造;19970722(07);46-49 * |
| 蠕变损伤 DZ411 合金恢复热处理组织演化;唐文书、肖俊峰等;航空材料学报;20190131;第39卷(第1期);70-78 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117660810A (en) | 2024-03-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111187946B (en) | Nickel-based wrought superalloy with high aluminum content and preparation method thereof | |
| CN108467972B (en) | Nickel-based wrought superalloy with high temperature bearing capacity and preparation method thereof | |
| CN110551920B (en) | High-performance easy-processing nickel-based wrought superalloy and preparation method thereof | |
| CN117684047B (en) | High-temperature alloy for turbine blade of gas turbine, and preparation method and application thereof | |
| CN112030040B (en) | High-niobium-content high-strength nickel-based wrought superalloy and preparation method thereof | |
| CN104630597A (en) | Iron-nickel-chromium-based superalloy and manufacturing method thereof | |
| CN115821117B (en) | GH4141 high-temperature alloy and preparation method thereof | |
| CN114196854A (en) | High-strength and difficult-to-deform nickel-based high-temperature alloy and preparation method thereof | |
| CN108467971A (en) | A kind of erosion resistant titanium alloy blade of aviation engine | |
| CN110983081B (en) | Method for preparing ultra-low oxygen cupronickel by adopting vacuum melting equipment | |
| CN115537603B (en) | High-temperature-resistant nickel-based alloy, manufacturing method and application thereof | |
| CN113106315B (en) | Nickel-chromium-aluminum alloy for heat-resisting 1200-degree heat exchange equipment and manufacturing method thereof | |
| CN117660810B (en) | High-purity high-temperature master alloy for variable-cycle gas engine turbine blade and preparation method and application thereof | |
| CN108531773A (en) | A kind of Ti3Al intermetallic compound high-temperature structural materials | |
| CN114645159B (en) | High-temperature oxidation-resistant high-strength nickel-tungsten-cobalt-chromium alloy and preparation method thereof | |
| CN114032420B (en) | High-performance cast high-temperature alloy | |
| CN111519069B (en) | High-strength nickel-cobalt-based high-temperature alloy and preparation process thereof | |
| EP3650560B1 (en) | Oxidation-resistant heat-resistant alloy and preparation method | |
| CN117363913B (en) | Low-carbon high-aluminum niobium-containing cobalt-based superalloy and preparation method thereof | |
| CN117363960B (en) | Low-carbon aluminum-free high-niobium-iron-based superalloy and preparation method thereof | |
| CN116219230B (en) | High-temperature alloy sealing plate material and preparation method thereof | |
| CN114921674B (en) | Vacuum induction melting method of 625 alloy | |
| CN118028660B (en) | Antioxidant corrosion-resistant cobalt-based superalloy, and preparation method and application thereof | |
| CN118086786B (en) | Seamless steel tube perforating plug and preparation method thereof | |
| CN115369272B (en) | Preparation method of suspension smelting high-melting-point Cr2Nb intermetallic compound |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |