US3816110A - Heat-resistant and corrosion-resistant high chromium-nickel alloy - Google Patents
Heat-resistant and corrosion-resistant high chromium-nickel alloy Download PDFInfo
- Publication number
- US3816110A US3816110A US00242799A US24279972A US3816110A US 3816110 A US3816110 A US 3816110A US 00242799 A US00242799 A US 00242799A US 24279972 A US24279972 A US 24279972A US 3816110 A US3816110 A US 3816110A
- Authority
- US
- United States
- Prior art keywords
- weight
- percent
- alloy
- resistant
- corrosion
- 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.)
- Expired - Lifetime
Links
- 229910000990 Ni alloy Inorganic materials 0.000 title abstract description 11
- 238000005260 corrosion Methods 0.000 title abstract description 11
- 230000007797 corrosion Effects 0.000 title abstract description 11
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 title abstract description 9
- 239000000956 alloy Substances 0.000 abstract description 28
- 229910045601 alloy Inorganic materials 0.000 abstract description 27
- 239000011651 chromium Substances 0.000 abstract description 18
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 abstract description 16
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 abstract description 15
- 229910052804 chromium Inorganic materials 0.000 abstract description 15
- 229910052796 boron Inorganic materials 0.000 abstract description 14
- 229910052715 tantalum Inorganic materials 0.000 abstract description 12
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 abstract description 9
- 229910052799 carbon Inorganic materials 0.000 abstract description 8
- 229910052750 molybdenum Inorganic materials 0.000 abstract description 8
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 abstract description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract description 6
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 abstract description 6
- 239000011733 molybdenum Substances 0.000 abstract description 6
- 229910052759 nickel Inorganic materials 0.000 abstract description 6
- 239000010936 titanium Substances 0.000 abstract description 6
- 229910052719 titanium Inorganic materials 0.000 abstract description 5
- 229910052782 aluminium Inorganic materials 0.000 abstract description 4
- 239000012535 impurity Substances 0.000 abstract description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 abstract description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract description 3
- 239000010763 heavy fuel oil Substances 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 238000005242 forging Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 abstract 1
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 description 6
- 238000007792 addition Methods 0.000 description 4
- 230000004580 weight loss Effects 0.000 description 4
- 230000003078 antioxidant effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 229910000601 superalloy Inorganic materials 0.000 description 3
- 229910052726 zirconium Inorganic materials 0.000 description 3
- 239000010941 cobalt Substances 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 230000001965 increasing effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052758 niobium Inorganic materials 0.000 description 2
- 229910052721 tungsten Inorganic materials 0.000 description 2
- -1 (Al Ti) Inorganic materials 0.000 description 1
- OYPRJOBELJOOCE-UHFFFAOYSA-N Calcium Chemical compound [Ca] OYPRJOBELJOOCE-UHFFFAOYSA-N 0.000 description 1
- 241000527994 Cyclotella gamma Species 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 238000002441 X-ray diffraction Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910052791 calcium Inorganic materials 0.000 description 1
- 239000011575 calcium Substances 0.000 description 1
- 238000012993 chemical processing Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000002516 radical scavenger Substances 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
Classifications
-
- 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
- C22C19/053—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 30% but less than 40%
Definitions
- ABSTRACT A heat-resistant and corrosion-resistant high chromium-nickel alloy, consisting of 32 to 40 percent by weight chromium, 2 to 9 percent by weight tantalum, 2 to 5 percent by weight molybdenum, 0.5 to 3 percent by weight (aluminum titanium), 0.05 to 0.5 percent by weight carbon, 0.025 to 0.35 percent by weight boron, with the remainder being substantially nickel and incidental impurities is provided.
- the maximum amount of chromium contained in the alloy was about 28 percent by weight, and usually no more than 20 percent by weight. While these additional quantities of chromium did have some beneficial effect in enhancing anti-oxidative properties, it was at best a compromise between enhanced antioxidative properties and reduced high temperature mechanical strength.
- Another object of this invention is to provide a structural material which is satisfactory for application in the construction of parts which will be subjected to high temperature and high stress service, such as gas turbine blades for turbines using low grade residual fuel oils.
- a high chromium-nickel alloy consisting of 32 to 40 percent by weight of chromium, 2 to 9 percent by weight tantalum, 2 to percent by weight molybdenum, 0.5 to 3 percent by weight (aluminum titanium), 0.05 to 0.5 percent by weight carbon, 0.025 to 0.35 percent by weight boron, with the remainder being substantially nickel and incidental impurities.
- the alloy of this invention may be a mixture of manganese, silicon, calcium, magnesium, rare earth elements and scavenger such as MISCI'I metal.
- Chromium, (aluminum titanium) and boron provide good high temperature corrosion-resistance. If the chromium content exceeds the upper limit of 40 percent, an a phase may appear in large quantities in solidification of the alloy. If the chromium content is less than 32 weight percent, satisfactory corrosionresistance will not be obtained. Chromium, tantalum, molybdenum and (aluminum titanium) improve the high temperature mechanical strength. In particular, tantalum has an outstanding ef fect on the high temperature mechanical strength.
- tantalum enables significant increases in high temperature mechanical strength while the use of chromium enables good corrosion-resistance. If the alloy contains greater than 9 weight per cent tantalum, there will be little increase in high temperature mechanical strength.
- Al titanium are the most effective additions to improve mechanical strength. The effectiveness of each of aluminum and titanium on the mechanical strength and corrosion-resistance is nearly equal. However, if amounts of greater than 3 weight percent are used, the alloy can become brittle and the long time stress rupture strength will diminish due to the appearance of an a phase.
- Carbon will decrease hardness of the alloy and increase elongation and is essential for long time stability of creep strength. More than 0.5 weight percent carbon, however, is undesirable because it will reduce the corrosion resistance of the alloy.
- the boron content of the alloy of this invention is greater than used in conventional alloys. If the boron content falls to below 0.025 weight percent, however, its effectiveness is reduced. On the contrary, if the boron content exceeds 0.35 weight percent, the alloy will become brittle.
- the alloy of this invention therefore, is characterized by excellent high temperature corrosion-resistance and excellent high temperature mechanical strength.
- the alloy of the invention will form a Gamma (7) phase matrix. Accordingly, it is desirable to heat treat the alloy to stabilize the structure, at a temperature adjacent to the use temperature to form the Gamma (-y) phase.
- EXAMPLE 1 mold to form the shape of a rod. After solution-treating Ti), C and B provided remarkable increases in the 10 high temperature mechanical strength.
- TABLE T ple was weighed into an alumina crucible and was melted by high frequency heating. The molten mass of alloy obtained was cast into a metal mold to form the shape of a rod. After solution-treating at a temperature of 1,220C. for 4 hours in order to form the f.c.c. Gamma (7 single phase structure, the rod was permitted to cool in air.
- test pieces were cut from the sound portion of the bar (or rod) by X-ray analysis, and were aged to stabilize the structure, at a temperature of Compositions of Samples Sam 1:: Composition bv we igl t) No r AI Mo Ta C B Ni
- A- I 31 36 0.5 1 4 5 0.2 0.2 Balance
- A-77 40 I 1 4 5 0.2 0.2 do.
- A-36 36 l 1 4 2 0.2 0.2 do.
- B-73 36 0 0 4 5 0.2 0.2 do.
- AW (mg/cm /hr.) is the corrosive weight loss per unit surface area per unit hour at l,l00C.
- Chromium imparts corrosion-resistance to these alloys of this invention, and saves mg/cm of corrosive weight loss per unit weight percent. Also, (aluminum .titanium) and boron effectively improve the corrosionresistance.
- Nb can be substituted for Ta
- Zr can be substituted for B
- W can be substituted for Mo.
- Nb and Zr are signifimay inferior to Ta or B in corrosion-resistance.
- W the effect of W on the tendency to promote Sigma (rr) phase is different from that of Mo.
- up t o 10 to 20 percent by weight of the Ta, B or Mo may be substituted by the elements Nb, Zr and W as above mentioned, and the similar characteristics will still be obtained.
- Cobalt in amounts of less than a few percent, may be substit uted for nickel.
- iron (Fe) it is necessary to avoid the addition of iron (Fe) to the alloy. If more than 2 to 3 percent by weight iron (Fe) is added to the alloy, the alloy will be severely hardened and will be more brittle in mechanical propert1es.
- a heat-resistant and corrosion-resistant high chromium-nickel alloy consisting essentially of 36 to 40 percent by weight chromium, 5 to 9 percent by weight tantalum, 2 to 5 percent by weight molybdenum, 0.5 to 3 percent by weight (aluminum titanium), 0.05 to 0.5
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP46023479A JPS5039046B1 (fr) | 1971-04-15 | 1971-04-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3816110A true US3816110A (en) | 1974-06-11 |
Family
ID=12111650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US00242799A Expired - Lifetime US3816110A (en) | 1971-04-15 | 1972-04-10 | Heat-resistant and corrosion-resistant high chromium-nickel alloy |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US3816110A (fr) |
| JP (1) | JPS5039046B1 (fr) |
| CH (1) | CH531568A (fr) |
| GB (1) | GB1371992A (fr) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111118348A (zh) * | 2019-12-31 | 2020-05-08 | 江苏新华合金有限公司 | 一种电热合金镍铬丝材的制备方法 |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110923512B (zh) * | 2019-12-04 | 2020-12-04 | 上海江竑环保科技有限公司 | 一种抗高温腐蚀的合金机芯、生产工艺及电磁加热回转窑 |
| CN114525430B (zh) * | 2022-03-03 | 2023-03-24 | 江苏奇纳新材料科技有限公司 | 一种镍基高温合金及其制备方法 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2570193A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | High-temperature alloys and articles |
| US2809139A (en) * | 1952-10-24 | 1957-10-08 | Research Corp | Method for heat treating chromium base alloy |
| US3015558A (en) * | 1959-09-16 | 1962-01-02 | Grant | Nickel-chromium-aluminum heat resisting alloy |
-
1971
- 1971-04-15 JP JP46023479A patent/JPS5039046B1/ja active Pending
-
1972
- 1972-04-10 US US00242799A patent/US3816110A/en not_active Expired - Lifetime
- 1972-04-13 GB GB1701072A patent/GB1371992A/en not_active Expired
- 1972-04-14 CH CH549172A patent/CH531568A/fr not_active IP Right Cessation
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2570193A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | High-temperature alloys and articles |
| US2809139A (en) * | 1952-10-24 | 1957-10-08 | Research Corp | Method for heat treating chromium base alloy |
| US3015558A (en) * | 1959-09-16 | 1962-01-02 | Grant | Nickel-chromium-aluminum heat resisting alloy |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111118348A (zh) * | 2019-12-31 | 2020-05-08 | 江苏新华合金有限公司 | 一种电热合金镍铬丝材的制备方法 |
Also Published As
| Publication number | Publication date |
|---|---|
| GB1371992A (en) | 1974-10-30 |
| JPS5039046B1 (fr) | 1975-12-13 |
| CH531568A (fr) | 1972-12-15 |
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