CN100543164C - A kind of directional solidification heat corrosion resistant nickel base cast superalloy and preparation method thereof - Google Patents
A kind of directional solidification heat corrosion resistant nickel base cast superalloy and preparation method thereof Download PDFInfo
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- CN100543164C CN100543164C CNB2007100110980A CN200710011098A CN100543164C CN 100543164 C CN100543164 C CN 100543164C CN B2007100110980 A CNB2007100110980 A CN B2007100110980A CN 200710011098 A CN200710011098 A CN 200710011098A CN 100543164 C CN100543164 C CN 100543164C
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 25
- 238000005260 corrosion Methods 0.000 title claims abstract description 14
- 230000007797 corrosion Effects 0.000 title claims abstract description 14
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 13
- 238000007711 solidification Methods 0.000 title claims abstract description 11
- 230000008023 solidification Effects 0.000 title claims abstract description 11
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 9
- 238000002360 preparation method Methods 0.000 title claims description 10
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 46
- 239000000956 alloy Substances 0.000 claims abstract description 46
- 238000001816 cooling Methods 0.000 claims abstract description 24
- 238000005275 alloying Methods 0.000 claims abstract description 9
- 238000002844 melting Methods 0.000 claims abstract description 9
- 230000008018 melting Effects 0.000 claims abstract description 9
- 229910001338 liquidmetal Inorganic materials 0.000 claims abstract description 8
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000007788 liquid Substances 0.000 claims abstract description 7
- 230000006698 induction Effects 0.000 claims abstract description 6
- 238000009413 insulation Methods 0.000 claims description 15
- 239000000470 constituent Substances 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 4
- 229910052684 Cerium Inorganic materials 0.000 abstract description 4
- 229910052758 niobium Inorganic materials 0.000 abstract description 3
- 230000002459 sustained effect Effects 0.000 abstract description 3
- 229910052726 zirconium Inorganic materials 0.000 abstract description 3
- 239000000126 substance Substances 0.000 abstract description 2
- 239000004615 ingredient Substances 0.000 abstract 1
- 239000013078 crystal Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 238000005266 casting Methods 0.000 description 3
- 229910052804 chromium Inorganic materials 0.000 description 2
- 238000005495 investment casting Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000002939 deleterious effect Effects 0.000 description 1
- 210000001787 dendrite Anatomy 0.000 description 1
- 238000006477 desulfuration reaction Methods 0.000 description 1
- 230000023556 desulfurization Effects 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000007669 thermal treatment Methods 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
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- Chemical & Material Sciences (AREA)
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- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of low-cost directional solidification heat corrosion resistant nickel base cast superalloy of excellent performance, the chemical ingredients scope (weight %) of alloy: C 0.04-0.09; Cr 14.5-15.3; Co 9.0-9.9; W 4.7-5.9; Mo 1.6-2.3; Al 2.8-3.3; Ti 4.2-5.0; Hf 0.3-0.6; Ta 0.3-1.5; B 0.06-0.10; Y (add-on) 0.015; Mn≤0.2; Si≤0.2; P≤0.008; S≤0.008; Fe≤0.5; Ni is surplus.Adopt the vacuum induction melting mother alloy, in liquid metal cooling (LMC) stove, carry out directional freeze, preparative column peritectic alloy, directed stove vacuum tightness≤5 * 10
-4MmHg, teeming temperature 1480-1570 ℃, drawing velocity 3-15mm/min, thermograde 95-145 ℃/cm, 250-350 ℃ of liquid tin temperature.The invention provides a kind of Ta of containing, and do not contain alloying element Re (low cost), Nb, Zr and Ce, and organize stable corrosion and heat resistant superalloy, compare tensile strength (σ with ч C88y-B и
b, σ
0.2) improve more than 30%, plasticity is obviously improved, and under same stress condition, sustained temperature improves 30 ℃, is suitable for making the turbine blade of gas turbine of 930 ℃ of uses.
Description
Technical field:
The present invention relates to the improvement technology of cast superalloy, be specially a kind of low-cost directional solidification heat corrosion resistant nickel base cast superalloy and preparation method thereof.
Background technology:
Document П а с п о р т П о О п л а в Ч С 88 у-В и (specification sheets of alloy Ч С 88 у-В и) points out that this alloy technology condition (Т у 14-1-4828-90) specified chemical composition is: C 0.04-0.09%; Cr15.4-16.3%; Co 10.0-11.5%; Mo 1.6-2.3%; W 4.7-5.9%; Al 2.8-3.3%; Ti 4.2-5.0%; Nb 0.1-0.3%; Hf 0.2-0.4%; B 0.06-0.10%; Zr (add-on) 0.03%; Y (add-on) 0.03%; Ce (add-on) 0.015%; Si≤0.3%; Mn≤0.3%; S≤0.008%; P≤0.008%; Fe≤0.5%; Ni is surplus.
This alloy adopts common precision casting process to prepare turbine blade of gas turbine, is organized as equiax crystal, is used to make the turbine moving blade that working temperature is not higher than 900 ℃.
Heat treatment of alloy technology is: 1170 ℃, and 4h, air cooling+1050 ℃, 4h, air cooling+850 ℃, 16h, air cooling.
The main mechanical property of this alloy is:
The weak point that above-mentioned alloy exists is: from mechanical property, this alloy can not be applicable to that working temperature is higher than 900 ℃ turbine blade of gas turbine, and cost of alloy is higher.
Summary of the invention:
The object of the present invention is to provide low-cost directional solidification heat corrosion resistant nickel base cast superalloy of a kind of excellent performance and preparation method thereof.
Technical scheme of the present invention is:
A kind of directional solidification heat corrosion resistant nickel base cast superalloy, by weight percentage, alloying constituent is as follows:
C 0.04-0.09%; Cr 14.5-15.3%; Co 9.0-9.9%; W 4.7-5.9%; Mo 1.6-2.3%; Al2.8-3.3%; Ti 4.2-5.0%; Hf 0.3-0.6%; Ta 0.3-1.5%; B 0.06-0.10%; Y (by add-on)≤0.015; Mn≤0.2%; Si≤0.2%; P≤0.008%; S≤0.008%; Fe≤0.5%; Ni is surplus.
Wherein, alloying element Y is by add-on.Micro-beneficial element (as rare earth element y, Ce etc.) in the superalloy is all pressed calculated amount usually and is added, and does not require and carry out composition analysis.These micro-parts be used for deoxidation and (or) desulfurization, and another part dissolves in solid solution matrix, and gathers partially in crystal boundary, plays the effect of reinforcement crystal boundary.Adding Y in the alloy of the present invention also is for same purpose.
Compare with Ч С 88 у-В и, alloy of the present invention does not contain Nb, Zr and Ce, contains the Ta of 0.3-1.5%, and Ч С 88 у-В и does not then contain Ta.Simultaneously, the composition range of Cr and Co is low in the alloy of the present invention, all outside the lower limit of the composition range of Ч С 88 у-В и.The content range of alloy Cr of the present invention is 14.5-15.3%, and Ч С 88 у-В и is 15.4-16.3%; Alloy Co content of the present invention is 9.0-9.9%, and Ч С 88 у-B и is 10.0-11.5%.In addition, the content of alloy Mn of the present invention and Si is lower.Like this, the formation proneness of TCP phase has reduced in the alloy of the present invention.N ν=2.562 of limitting in Ч С 88 у-В и alloying constituent, this alloy is N ν=2.431, is lower than the critical electron vacancy number 2.50 that the σ phase occurs.
The thought of design of alloy of the present invention is to add hot strength and creep rupture strength that Ta improves alloy, reinforcement γ ' phase because most of Ta dissolves in γ ' phase, the precipitation strength effect of increase γ ' phase; Simultaneously, the Ta of small portion enters the γ matrix, plays the solution strengthening effect, and Ta replaces Nb can also improve hot corrosion resistance, the disadvantageous effect that compensation brings hot corrosion resistance owing to the suitable reduction of Cr content.And suitably reduce Cr and Co content, and be for when keeping the good resistance hot corrosion resistance, reduce the average electron vacancy number of alloy, suppress σ to separate out mutually, improve the structure stability of alloy high-temp life-time service.Not adding Zr is in order to eliminate the hot cracking tendency in the directional freeze process.
In addition, by technological measure, change directional freeze into by common precision casting, particularly adopt current external state-of-the-art liquid metal refrigerative directional solidification processes, not only eliminated deleterious horizontal crystal boundary, and made and organize refinement more, evenly, collimation is better.Add and adopt the heat treating regime of optimizing to heat-treat that make the alloy excellent combination property of being invented, use temperature improves 30 ℃ than Ч С 88 у-В и, can be at 930 ℃ of life-time service.
The present invention also provides the preparation method of this alloy, adopts the vacuum induction melting mother alloy, carries out directional freeze in liquid metal cooling (LMC) stove, preparation directional columnargrain alloy, directed stove vacuum tightness≤5 * 10
-4MmHg, teeming temperature 1480-1570 ℃, drawing velocity 3-15mm/min, thermograde 95-145 ℃/cm, 250-350 ℃ of liquid tin temperature.
The thermal treatment process that alloy of the present invention adopts is:
(1) 1160-1220 ℃, insulation 2-4h, air cooling is to room temperature;
(2) 1030-1120 ℃, insulation 2-4h, air cooling is to room temperature;
(3) 830-880 ℃, insulation 16-24h, air cooling is to room temperature.
Beneficial effect of the present invention is as follows:
1, the invention provides a kind of Ta of containing, and do not contain alloying element Re (low cost), Nb, Zr and Ce, and organize stable corrosion and heat resistant superalloy.Compare tensile strength (σ with Ч С 88 у-В и
b, σ
0.2) improve more than 30%, plasticity is obviously improved, and under same stress condition, sustained temperature improves 30 ℃, is suitable for making the turbine blade of gas turbine of 930 ℃ of uses.
2, alloy of the present invention is the directional columnargrain alloy that adopts the preparation of liquid metal cooling (LMC) directional solidification processes, and is completely different with the equiax crystal of Ч С 88 у-В и.Concrete technology is vacuum tightness≤5 * 10
-4MmHg, teeming temperature 1480-1570 ℃; Drawing velocity 3-15mm/min; Thermograde 95-145 ℃/cm; The temperature 250-350 of liquid tin ℃.
3, the enduring quality of alloy of the present invention sustained temperature under kindred circumstances improves 30 ℃.
Description of drawings:
Fig. 1 is the horizontal and vertical tissue of LMC directional solidificating alloy of the present invention; (a) horizontal, (b) vertical.
Embodiment:
Embodiment 1
By weight percentage, alloying constituent is: C 0.07%; Cr 14.8; Co 9.5%; W 5.1%; Mo 1.8%; Al 3.1%; Ti 4.6%; Hf 0.46%; Ta 0.8%; B 0.08%; Y (add-on) 0.015%; Mn 0.18%; Si 0.18%; P 0.006%; S 0.007%; Fe 0.3%; Ni is surplus.
The melting of alloy and casting:, carry out directional freeze, directed stove vacuum tightness≤5 * 10 with liquid metal cooling (LMC) technology with 25kg vacuum induction melting mother alloy
-4MmHg, 1540 ℃ of teeming temperatures, drawing velocity 10mm/min, 100 ℃/cm of thermograde, 270 ℃ of the temperature of liquid tin.
The heat treatment of alloy system: 1170 ℃, insulation 4h, air cooling+1050 ℃, insulation 4h, air cooling+850 ℃, insulation 16h, air cooling.
The main mechanical property of alloy:
Room temperature tensile performance: σ
b1320MPa; σ
0.2990MPa; δ 8%;
4.0%.
Enduring quality: 930 ℃, stress 270MPa, duration τ 150.5h, δ 20.8%.
The horizontal and vertical tissue of LMC directional solidificating alloy of the present invention is shown in Fig. 1 (a) and Fig. 1 (b), and as can be seen, dendrite is tiny and be arranged in parallel.
Embodiment 2
By weight percentage, alloying constituent is: C 0.045%; Cr 14.7; Co 9.2%; W 4.85%; Mo 1.72%; Al 2.85%; Hf 0.35%; Ti 4.35%; Ta 0.4%; B 0.07%; Y (add-on) 0.015%; Mn 0.12%; Si 0.10%; P 0.006%; S 0.005%; Fe 0.2%; Ni is surplus.
Alloy melting and casting with 25kg vacuum induction melting mother alloy, are carried out directional freeze, directed stove vacuum tightness≤5 * 10 with liquid metal cooling (LMC) technology
-4MmHg, 1520 ℃ of teeming temperatures, drawing velocity 8mm/min, 95 ℃/cm of thermograde, 300 ℃ of the temperature of liquid tin.
Heat treating regime is: 1200 ℃, and insulation 2h, air cooling+1090 ℃, insulation 2h, air cooling+850 ℃, insulation 24h, air cooling.
The main mechanical property of alloy:
Room temperature tensile performance: σ
b1330MPa; σ
0.21040MPa; δ 8.0%;
9.5%.
Enduring quality: 930 ℃, stress 270MPa, τ 117.3h.
Embodiment 3
By weight percentage, alloying constituent is: C 0.08%; Cr 15.3%; Co 9.9%; W 5.7%; Mo2.2%; Al 3.2%; Ti 4.9%; Hf 0.55%; Ta 1.3%; B 0.09%; Y (add-on) 0.015%; Mn 0.19%; Si 0.18%; P 0.007%; S 0.008%; Fe 0.4%; Ni is surplus.
The melting of alloy and casting:, carry out directional freeze, directed stove vacuum tightness≤5 * 10 with liquid metal cooling (LMC) technology with 25kg vacuum induction melting mother alloy
-4MmHg, 1500 ℃ of teeming temperatures, drawing velocity 12mm/min, 110 ℃/cm of thermograde, 270 ℃ of the temperature of liquid tin.
The heat treatment of alloy system: 1170 ℃, insulation 4h, air cooling+1050 ℃, insulation 4h, air cooling+850 ℃, insulation 16h, air cooling.
Room temperature tensile performance: σ
b1340MPa; σ
0.21110MPa; δ 5.5%;
7.5%.
Enduring quality: 930 ℃, stress 270MPa, τ 124.8h.
Claims (3)
1, a kind of directional solidification heat corrosion resistant nickel base cast superalloy is characterized in that, by weight percentage, alloying constituent is as follows:
C 0.04-0.09%; Cr 14.5-15.3%; Co 9.0-9.9%; W 4.7-5.9%; Mo 1.6-2.3%; Al2.8-3.3%; Ti 4.2-5.0%; Hf 0.3-0.6%; Ta 0.3-1.5%; B 0.06-0.10%; Y is by add-on≤0.015; Mn≤0.2%; Si≤0.2%; P≤0.008%; S≤0.008%; Fe≤0.5%; Ni is surplus.
2, according to the preparation method of the described directional solidification heat corrosion resistant nickel base cast superalloy of claim 1, it is characterized in that:
Adopt the vacuum induction melting mother alloy, in the liquid metal cool furnace, carry out directional freeze then, preparation directional columnargrain alloy; Directed stove vacuum tightness≤5 * 10
-4MmHg, teeming temperature 1480-1570 ℃, drawing velocity 3-15mm/min, thermograde 95-145 ℃/cm, 250-350 ℃ of liquid tin temperature.
According to the preparation method of the described directional solidification heat corrosion resistant nickel base cast superalloy of claim 2, it is characterized in that 3, heat treatment of alloy is carried out as follows:
(1) 1160-1220 ℃, insulation 2-4h, air cooling is to room temperature;
(2) 1030-1120 ℃, insulation 2-4h, air cooling is to room temperature;
(3) 830-880 ℃, insulation 16-24h, air cooling is to room temperature.
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| Application Number | Priority Date | Filing Date | Title |
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| CNB2007100110980A CN100543164C (en) | 2007-04-25 | 2007-04-25 | A kind of directional solidification heat corrosion resistant nickel base cast superalloy and preparation method thereof |
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| CNB2007100110980A CN100543164C (en) | 2007-04-25 | 2007-04-25 | A kind of directional solidification heat corrosion resistant nickel base cast superalloy and preparation method thereof |
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| CN100543164C true CN100543164C (en) | 2009-09-23 |
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Cited By (1)
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|---|---|---|---|---|
| RU2567759C2 (en) * | 2010-09-20 | 2015-11-10 | Сименс Акциенгезелльшафт | Nickel-based superalloy |
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| CN115558823A (en) * | 2022-10-24 | 2023-01-03 | 江苏星火特钢集团有限公司 | Nickel-based high-temperature alloy with excellent high-temperature mechanical and thermal fatigue properties and preparation method thereof |
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| RU2567759C2 (en) * | 2010-09-20 | 2015-11-10 | Сименс Акциенгезелльшафт | Nickel-based superalloy |
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