CN101372730A - Gamma''strengthened high performance casting nickel-based high-temperature alloy - Google Patents
Gamma''strengthened high performance casting nickel-based high-temperature alloy Download PDFInfo
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Abstract
The invention provides a gamma' intensified high-performance cast nickel-based high-temperature alloy, which is characterized in that the alloy comprises the compositions by weight percentage as follows: 0.007 to 0.07 percent of C, 0.007 to 0.09 percent of B, 0 to 0.10 percent of Ce, 0 to 0.10 percent of Y, 10.0 to 15.0 percent of Co, 15.0 to 20.0 percent of Cr, 1.0 to 4.0 percent of Mo, 0.2 to 3.0 percent of Al, 0.5 to 3.0 percent of Ti, 0 to 3.0 percent of W, 2.0 to 6.0 percent of Nb, 0 to 6.0 percent of Ta, and the residual amount of Ni, wherein, the contents of impurities by weight percentage are as follows: less than or equal to 0.01 percent of S, less than or equal to 0.01 percent of P, less than or equal to 0.2 percent of Si, less than or equal to 0.0005 percent of Pb, less than or equal to 0.0001 percent of Bi, less than or equal to 0.2 percent of Mn, and less than or equal to 0.5 percent of Fe. The invention changes the alloying compositions, not only has higher high-temperature mechanical performance, but also has excellent long-term application structural stability at 700 DEG C, and can meet the requirement of a cartridge receiver of an airspace engine or an aero-engine with higher service temperature and higher performance requirement.
Description
Technical field
The present invention relates to industrial technology-metallic substance science, a kind of γ be provided especially " high performance casting nickel-based high-temperature alloy strengthened.
Background technology
Inconel 718 alloys are that the H.L.Eiselstein by huntington branch office (Huntington) of U.S. International nickel Co. Ltd. Inco. Ltd. (INCO Alloys International) succeeds in developing, and it is open in nineteen fifty-nine, be a kind of with body-centered teteragonal Ni3Nb (γ ") and face-centered cubic Ni3 (Al; Ti, Nb) nickel-chromium-iron-based wrought superalloy of (γ ') precipitation strength.This alloy has high tensile strength, yield strength, creep rupture strength and plasticity between-253～650 ℃, have good anticorrosive, anti-irradiation, hot-work and welding property simultaneously.
Under the background of superalloy integral precision casting technology high-speed development, initial Inconel 718 alloys that grow up as wrought superalloy also began to be applied to the aerospace industry with the casting alloy form from nineteen sixty-five, and the corresponding casting alloy trade mark is Inconel 718C.In recent years, development along with large-scale hot isostatic pressing (HIP) equipment that adapts to massive casting production, and the going deep into of technical studies such as repair welding and casting postheat treatment, more complex construction, large-scale Inconel 718C structural casting manufacturing process that more thin-walled is thick reach its maturity, the soldering group component that replaces forging gradually is widely used in the manufacturing field of the parts such as turbo-pump housing of various aero-engine casings and airspace engine.
China begins imitated Inconel 718 alloys in nineteen sixty-eight, and the domestic trade mark is GH4169.As the imitated model of cast superalloy Inconel 718C, China has developed the K4169 alloy, and Preliminary Applications in parts such as aircraft engine monoblock casting diffuser-casing and heavy ring.
Although Inconel 718 alloy property excellences, but because its main strengthening phase γ "-Ni3Nb is metastable phasing; when temperature surpasses about 650 ℃; γ " and the alligatoring of growing up rapidly, and change into its stable phase δ, cause alloy strength and creep rupture life to descend rapidly, thereby the general only permission of this alloy is at 650 ℃ of following life-time service.
The present invention is directed to alloy γ for this reason " phase stability is poor; easily change the problem that δ reduces alloy property mutually into; it is suitable with 650 ℃ of intensity of Inconel 718C (K4169) alloy to develop a kind of 700 ℃ of strength levels, and after 700 ℃ of long-term timeliness, still can keep organizing the new alloy with stable performance.
Summary of the invention
The objective of the invention is in order to overcome K4169 alloy working temperature and to surpass about 650 ℃, the shortcoming that alloy strength and creep rupture life descend rapidly provides a kind of γ especially " high performance casting nickel-based high-temperature alloy strengthened.
The invention provides a kind of γ " high performance casting nickel-based high-temperature alloy strengthened, it is characterized in that: the alloying constituent weight percent is as follows: C:0.007-0.07; B:0.007-0.09; Ce:0-0.10; Y:0-0.10; Co:10.0-15.0; Cr:15.0-20.0; Mo:1.0-4.0; Al:0.2-3.0; Ti:0.5-3.0; W:0-3.0; Nb:2.0-6.0; Ta:0-6.0; The Ni surplus; Foreign matter content: S≤0.01 wherein, P≤0.01, Si≤0.2, Pb≤0.0005, Bi≤0.0001, Mn≤0.2, Fe≤0.5.
The invention alloy is a cast superalloy.By to the content that reduces the Nb element to reduce and to suppress the solidifying segregation of alloying element, reduce the solidification temperature range of invention alloy.Fig. 1 shows that No.1 alloy graining interval is 60 ℃, is significantly less than the about 100 ℃ freezing range of Inconel 718 alloys, and this helps improving the alloy casting processing performance.
Invention alloy room temperature to 700 ℃ intensity surpasses Inconel 718C (K4169) and Rene220 alloy comprehensively, 700 ℃ of intensity and Inconel 718C (K4169) and Rene 220 alloy room temperature strengths are on close level, enduring quality also significantly improves, and the invention alloy is after 700 ℃ of 1000 hours timeliness, room temperature and 700 ℃ of tensile strengths further improve, enduring quality also keeps with timeliness before be on close level.
As seen from Figure 1,1290 ℃ of No.1 alloy graining peak temperatures, 1350 ℃ of final temperature of solidification, the freezing range scope is 60 ℃.
This advantage: alloy of the present invention possesses favorable tissue stability at 700 ℃, possesses excellent room temperature to 700 ℃ tensile property and 700 ℃ of enduring qualities, can satisfy the demand of the aircraft engine integral precision casting casing of higher use temperature and performance requriements.
Description of drawings
Fig. 1 is the DSC curve in alloy of the present invention (No.1 alloy) process of setting, and cooling rate speed is 5 ℃/min.
Embodiment
Embodiment 1
Alloy of the present invention (No.1 alloy), alloying constituent is as shown in table 1.
The employing smelting technology is: the clear back 1500 ℃ of refinings of mother alloyization 10 minutes are cooled to 1400 ℃ of cast, 800 ℃ of shell temperature.The employing heat treating regime is: 1180 ℃, and 4 hours, air cooling → 775 ℃, 4 hours, stove was chilled to 700 ℃ → 700 ℃, and 10 hours, air cooling.
Table 1 No.1 alloying constituent, wt%
| Cr | Co | A1 | Ti | Nb | Ta | Mo | C | B | Y | Ni |
| 18.0 | 12.0 | 0.5 | 1.0 | 4.0 | 3.0 | 3.0 | 0.015 | 0.020 | 0.05 | Bal |
Table 2 No.1 alloy mechanical property and with the K4169 performance comparison
No.1 alloy mechanical property and as shown in table 2 with the K4169 performance comparison.As seen: the No.1 alloy room temperature tensile yield strength of invention and breaking tenacity improve little than K4169 alloy, but 700 ℃ of tensile strengths and 700 ℃/580MPa all are significantly increased than K4169 alloy creep rupture life.
No.2 alloying constituent of the present invention sees Table 3, and smelting and thermal treatment process are with embodiment 1.
Table 3 No.2 alloying constituent, wt%
| Cr | Co | A1 | Ti | Nb | Ta | Mo | C | B | Y | Ni |
| 18.0 | 12.0 | 0.5 | 1.0 | 3.0 | 5.0 | 3.0 | 0.015 | 0.020 | 0.05 | Bal |
No.2 alloy mechanical property of the present invention and as shown in table 4 with the K4169 performance comparison.As seen: No.2 alloy room temperature, 700 ℃ of tensile yield strengths and breaking tenacity and 700 ℃/580MPa all are significantly increased than K4169 alloy creep rupture life.
Table 4 No.2 alloy mechanical property and with the K4169 performance comparison
No.3 alloying constituent of the present invention sees Table 5, and smelting and thermal treatment process are with embodiment 1.
Table 5 No.3 alloying constituent, wt%
| Cr | Co | Al | Ti | Nb | Ta | Mo | W | C | B | Y | Ni |
| 18.0 | 12.0 | 0.5 | 1.0 | 3.0 | 5.0 | 3.0 | 2.0 | 0.01 5 | 0.02 0 | 0.05 | Bal |
No.3 alloy mechanical property of the present invention and as shown in table 6 with the K4169 performance comparison.As seen: No.3 alloy room temperature, 700 ℃ of tensile yield strengths and breaking tenacity and 700 ℃/580MPa all are significantly increased than K4169 alloy creep rupture life.
Table 6 No.3 alloy mechanical property and with the K4169 performance comparison
Embodiment 4:
No.4 alloying constituent of the present invention sees Table 7, and smelting and thermal treatment process are with embodiment 1.
Table 7 No.4 alloying constituent, wt%
| Cr | Co | Al | Ti | Nb | Ta | Mo | W | C | B | Y | Ni |
| 18.0 | 12.0 | 0.5 | 1.0 | 3.0 | 5.0 | 2.0 | 2.0 | 0.015 | 0.020 | 0.05 | Bal |
No.4 alloy mechanical property of the present invention and as shown in table 8 with the K4169 performance comparison.As seen: No.4 alloy room temperature, 700 ℃ of tensile yield strengths and breaking tenacity and 700 ℃/580MPa all are significantly increased than K4169 alloy creep rupture life.
Table 8 No.4 alloy mechanical property and with the K4169 performance comparison
Embodiment 5:
The No.1 alloy by embodiment 1 smelt with thermal treatment after, carry out 700 ℃ of long-term timeliness of 1000h again, carry out 700 ℃/620MPa enduring quality test subsequently, enduring quality the results are shown in Table 9 before and after the long-term timeliness.As seen, the No.1 alloy does not only reduce before 700 ℃ of 1000 hours long-term timeliness enduring qualities are than long-term timeliness, increases on the contrary.
700 ℃/620MPa enduring quality contrast before and after the long-term timeliness of table 9 No.1 alloy
| State | T/h | δ 5，％ |
| Conventional thermal treatment | 124 | 2.0 |
| 700 ℃ of 1000 hours long-term timeliness | 191 | 2.0 |
Embodiment 6:
No.4 alloy of the present invention, smelt and thermal treatment process with embodiment 1, the tensile property under its differing temps and as shown in table 10 with the performance comparison of K4169 alloy.As seen No.4 alloy of the present invention all is significantly higher than the K4169 alloy in the surrender and the breaking tenacity of 25～700 ℃ of each temperature.
Tensile property contrast under table 10 No.4 alloy and the K4169 alloy differing temps
Embodiment 7:
The No.4 alloy by embodiment 1 smelt with thermal treatment after, carry out 700 ℃ of long-term timeliness of 500h again, carry out 700 ℃/620MPa enduring quality test subsequently, enduring quality the results are shown in Table 11 before and after the long-term timeliness.As seen, this alloy does not only reduce before 700 ℃ of 500 hours long-term timeliness enduring qualities are than long-term timeliness, increases on the contrary.
700 ℃/620MPa enduring quality contrast before and after the long-term timeliness of table 11 No.4 alloy
| State | τ/h | δ 5，％ |
| Conventional thermal treatment | 250 | 1.0 |
| 700 ℃ of 500 hours long-term timeliness | 302 | 3.0 |
Claims (1)
1. γ " high performance casting nickel-based high-temperature alloy strengthened, it is characterized in that: the alloying constituent weight percent is as follows: C:0.007-0.07; B:0.007-0.09; Ce:0-0.10; Y:0-0.10; Co:10.0-15.0; Cr:15.0-20.0; Mo:1.0-4.0; Al:0.2-3.0; Ti:0.5-3.0; W:0-3.0; Nb:2.0-6.0; Ta:0-6.0; The Ni surplus; Foreign matter content: S≤0.01 wherein, P≤0.01, Si≤0.2, Pb≤0.0005, Bi≤0.0001, Mn≤0.2, Fe≤0.5.
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| CN102041412A (en) * | 2009-10-21 | 2011-05-04 | 通用电气公司 | Nickel-containing alloys, method of manufacture thereof and articles derived thereform |
| CN102433466A (en) * | 2010-09-29 | 2012-05-02 | 中国科学院金属研究所 | Nickel and cobalt-based high-temperature alloy containing rare earth elements and preparation method thereof |
| CN102534307A (en) * | 2012-02-14 | 2012-07-04 | 于学勇 | High-strength nickel-cobalt-based high-damping alloy |
| CN102605278A (en) * | 2012-03-13 | 2012-07-25 | 周子超 | High-temperature alloy and hot isostatic pressing sintering method thereof |
| CN102808114A (en) * | 2012-08-24 | 2012-12-05 | 叶绿均 | Nickel-based superalloy |
| CN103074525A (en) * | 2013-02-27 | 2013-05-01 | 南京信息工程大学 | Nickel-based high-temperature-resistant alloy material and preparation method thereof |
| CN103074526A (en) * | 2013-02-27 | 2013-05-01 | 南京信息工程大学 | Ni-base alloy material and preparation method thereof |
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| US7156932B2 (en) * | 2003-10-06 | 2007-01-02 | Ati Properties, Inc. | Nickel-base alloys and methods of heat treating nickel-base alloys |
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