US2542962A - Nickel aluminum base alloys - Google Patents
Nickel aluminum base alloys Download PDFInfo
- Publication number
- US2542962A US2542962A US39581A US3958148A US2542962A US 2542962 A US2542962 A US 2542962A US 39581 A US39581 A US 39581A US 3958148 A US3958148 A US 3958148A US 2542962 A US2542962 A US 2542962A
- Authority
- US
- United States
- Prior art keywords
- nickel
- aluminium
- alloy
- cobalt
- molybdenum
- 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
- 229910045601 alloy Inorganic materials 0.000 title claims description 23
- 239000000956 alloy Substances 0.000 title claims description 23
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 title claims description 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 44
- 229910052759 nickel Inorganic materials 0.000 claims description 22
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 14
- 239000004411 aluminium Substances 0.000 description 13
- 229910052782 aluminium Inorganic materials 0.000 description 13
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 13
- 239000010941 cobalt Substances 0.000 description 13
- 229910017052 cobalt Inorganic materials 0.000 description 13
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 13
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 10
- 229910052750 molybdenum Inorganic materials 0.000 description 10
- 239000011733 molybdenum Substances 0.000 description 10
- 229910052751 metal Inorganic materials 0.000 description 9
- 239000002184 metal Substances 0.000 description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 7
- 229910052799 carbon Inorganic materials 0.000 description 7
- 229910052742 iron Inorganic materials 0.000 description 7
- 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 4
- 150000002739 metals Chemical class 0.000 description 4
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 3
- 239000010955 niobium Substances 0.000 description 3
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 3
- 229910052710 silicon Inorganic materials 0.000 description 3
- 239000010703 silicon Substances 0.000 description 3
- 229910052715 tantalum Inorganic materials 0.000 description 3
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 3
- 229910052721 tungsten Inorganic materials 0.000 description 3
- 239000010937 tungsten Substances 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000003750 conditioning effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 229910052723 transition metal Inorganic materials 0.000 description 2
- 150000003624 transition metals Chemical class 0.000 description 2
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 229960005419 nitrogen Drugs 0.000 description 1
- 229910021652 non-ferrous alloy Inorganic materials 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000006467 substitution reaction 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
Definitions
- aluminium may vary between 25 and 6.
- This invention relates to non-ferrous alloys and particularly to nickel-aluminium base alloys which have high strength and superior resistance to creep and oxidation at high temperatures, and
- the base of such alloys is nickel and aluminium but cobalt could be substituted for part of the nickel provided the ratio of nickel to cobalt is no less than 4. That is to say not more than 20% of the nickel may be replaced with cobalt.
- the ratio of nickel to aluminium (or nickel plus cobalt to) should be stated that properties of cobalt are similar to those of nickel in many respects but in an alloy containing aluminium it does not behave the same as nickel in all respects. Thus the substitution of cobalt for nickel must be confined withi the limits stated for the purpose of the present alloys.
- the oxide of this added metal should not be so volatile at the service temperature as to substantially reduce the ability of the surface of the alloy to resist corrosion.
- the service temperature may be in excess of 800 C.
- Tungsten, tantalum and columbium meet these requirements to a somewhat greater degree than molybdenum.
- molybdenum is more readily available and economical.
- An alloy of the invention contains at least 10% and not more than 30% molybdenum. If two or more of these conditioning metals are used the minimum amount is 10% but the upper limit may be 35%.
- the metals incorporated in these alloys may contain traces or minor portions of so-called tramp elements, such as iron, manganese, silicon, carbon, nitro gen and the like, which may thus appear in the 2 alloys.
- tramp elements such as iron, manganese, silicon, carbon, nitro gen and the like, which may thus appear in the 2 alloys.
- Iron should not be present in excess of 1%, manganese in excess of- 0.5% or carbon in excess of 0.15% and the total of such tramp constituents should not substantially exceed 2% of the weight of the alloy.
- the alloy contains the following elements in the following percent.- ages of the weight of the whole alloy:
- this alloy will support a tensile stress of 36,000, 26,000 and 20,000 p. s. i. for 100, 1000 and 5000 hours respectively before fracture occurs.
- the respective creep rates are 0.0025, 0.0016 and 0.0008 per cent per hour.
- a tensile stress of 22,000 p. s. i. which produces a minimum creep rate of 0.001 per cent per hour at 815 C. will not cause fracture in less than 3000 hours.
- a nickel aluminium base alloy consisting of 54.00 to 81.74% nickel plus cobalt, the weight ratio of nickel to cobalt being not less than '4, 2.42 to 12.14% aluminium, the weight ratio of nickel plus cobalt to aluminium being not more than 25 nor less than 6, 10 to 35% two addition metals from the group consisting of molybdenum, tungsten, tantalum and columbium, and not substantially more tha 2% of all other elements including not substantially more than 1 iron, 0.5% manganese, 0.15% carbon.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Supercharger (AREA)
Description
aluminium) may vary between 25 and 6.
Patented Feb. 20, 1951 NICKEL ALUMINlLlM BASE ALLOYS Harold V. Kinsey, Manor Park Village, Ontario, Canada, assignor to His Majesty the Kingin the right of Canada, as represented by the Mnister of Mines and Technical Surveys No Drawing. Application July 19, 1948',
.. Serial No. 39,581
6 Claims. (01. 75-170) This invention relates to non-ferrous alloys and particularly to nickel-aluminium base alloys which have high strength and superior resistance to creep and oxidation at high temperatures, and
which are particularly adapted to withstand the effect oflong exposure to hot combustion gases as for example when used in the form of blades for the hot end of gas turbine engines.
In accordance with the invention the base of such alloys is nickel and aluminium but cobalt could be substituted for part of the nickel provided the ratio of nickel to cobalt is no less than 4. That is to say not more than 20% of the nickel may be replaced with cobalt. The ratio of nickel to aluminium (or nickel plus cobalt to It should be stated that properties of cobalt are similar to those of nickel in many respects but in an alloy containing aluminium it does not behave the same as nickel in all respects. Thus the substitution of cobalt for nickel must be confined withi the limits stated for the purpose of the present alloys.
Applicant has found that the addition to this metal base of the transition metals now to be defined provides an alloy which has high tensile strength and at the same time highresistance to creep, both of which properties are critically important in stressed metal structures ,orparts which are required to remain dimensionally stable under high temperatures and in the presence of corrosive gases.
Thus, in accordance with the invention, there is added to the above-described metal base a transition metal having the alloying characteristics of molybdenum. It is essential that the oxide of this added metal should not be so volatile at the service temperature as to substantially reduce the ability of the surface of the alloy to resist corrosion.- The service temperature may be in excess of 800 C. Tungsten, tantalum and columbium meet these requirements to a somewhat greater degree than molybdenum. However, molybdenum is more readily available and economical.
An alloy of the invention contains at least 10% and not more than 30% molybdenum. If two or more of these conditioning metals are used the minimum amount is 10% but the upper limit may be 35%.
It will be recognized that the metals incorporated in these alloys may contain traces or minor portions of so-called tramp elements, such as iron, manganese, silicon, carbon, nitro gen and the like, which may thus appear in the 2 alloys. Iron should not be present in excess of 1%, manganese in excess of- 0.5% or carbon in excess of 0.15% and the total of such tramp constituents should not substantially exceed 2% of the weight of the alloy.
According to the invention the alloy contains the following elements in the following percent.- ages of the weight of the whole alloy:
Per cent Nickel (or nickel and cobalt) 5400451374 Aluminium 24-2-1214 Conditioning metal 10.00-35.00
Tramp elements Not more than 2.00
The following are specific examples of the alloy:
(1) Nickel 75.2, aluminium 8.4, molybdenum 15.8, iron 0.4, silicon 0.24, carbon 0.03. At a temperature of 815 C. this alloy will support a tensile stress of 36,000, 26,000 and 20,000 p. s. i. for 100, 1000 and 5000 hours respectively before fracture occurs. At this stress the respective creep rates are 0.0025, 0.0016 and 0.0008 per cent per hour. A tensile stress of 22,000 p. s. i. which produces a minimum creep rate of 0.001 per cent per hour at 815 C. will not cause fracture in less than 3000 hours.
(2) Nickel 66.5, aluminium 7.0, molybdenum 25.5, iron 0.8, silicon 0.16 and carbon 0.03. At a temperature of 815 C. this alloy will support a tensile stress of 40,000, 27,000 and 21,000 p. s. i. for 100, 1000 and 5000 hours respectively before fracture occurs. At this stress the respective creep rates are 0.0033, 0.0022 and 0.0011 per cent per hour. A tensile stress of 26,000 p. s. i. which produces a minimum creep rate of 0.002 per cent per hour at 815 C. will not cause fracture in less than 1200 hours. At room temperature bars of this alloy have a tensile strength of 130,000 p. s. i. and a Vickers hardness value (30-kg. load) of 391.
Analysis and examination of such alloys from various points of view show that the presence of molybdenum, or other of the modifying metals defined, in the proportions specified produce a pronounced effect in increasing the strength and of molybdenum, tungsten, tantalum and columbium and, not more than substantially 2% of all other elements including not substantially more than 1% iron, 0.5% manganese, 0.15% carbon.
2. A nickel aluminium base alloy consisting of 54.00 to 81.74% nickel plus cobalt, the weight ratio of nickel to cobalt being not less than '4, 2.42 to 12.14% aluminium, the weight ratio of nickel plus cobalt to aluminium being not more than 25 nor less than 6, 10 to 35% two addition metals from the group consisting of molybdenum, tungsten, tantalum and columbium, and not substantially more tha 2% of all other elements including not substantially more than 1 iron, 0.5% manganese, 0.15% carbon.
3. An alloy consisting of 54.00 to 81.74% nickel,
2.42 to 12.14% aluminium, 10 to 30% of molyb-i denum, and ot substantially more than 2% of all other elements, including not substantially more than 1% iron, 0.5% manganese, 0.15% carbon and the ratio of nickel to aluminium by weight being between 25 and 6. V
4. An alloy consisting of 54.00 to 81.74% ickel plus cobalt, the weight ratio of nickel to cobalt being not less than 4,242 to 12.14% aluminium,
the weight ratio of nickel plus cobalt to aluminium being not more than 25 nor less than 6, 10 to 30% molybdenum and not substantially more than 2% of all other elements including not sub- 7 REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 1,277,046 Cooper -1 Aug. 27, 1918 1,803,468 Driver May 5, 1931 1,924,245 Koster "Aug. 29, 1933 2,071,645 McNeil Feb; 23, 1937- 2,460,590 Lohr Feb. 1,1949
A FOREIGN PATENTS Number Country Date 127,930 Great Britain June 10, 1949 425,614 Great Britain Mar. 15,1935 583,841 Great Britain Jan. 1, 1947 698,724
France Nov. 29, 1930
Claims (1)
1. A NICKEL ALUMINIUM BASE ALLOY CONSISTING OF 54.00 TO 81.74% NICKEL, 2.42 TO 12.14% ALUMI
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US39581A US2542962A (en) | 1948-07-19 | 1948-07-19 | Nickel aluminum base alloys |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US39581A US2542962A (en) | 1948-07-19 | 1948-07-19 | Nickel aluminum base alloys |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2542962A true US2542962A (en) | 1951-02-20 |
Family
ID=21906229
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US39581A Expired - Lifetime US2542962A (en) | 1948-07-19 | 1948-07-19 | Nickel aluminum base alloys |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2542962A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3330633A (en) * | 1964-06-26 | 1967-07-11 | United Aircraft Corp | Coatings for high-temperature alloys |
| US3403996A (en) * | 1965-09-17 | 1968-10-01 | Matsushita Electric Industrial Co Ltd | Ferromagnetic material |
| US3429697A (en) * | 1967-03-30 | 1969-02-25 | Gen Electric | Process for producing cobalt-aluminum bodies |
| US3617397A (en) * | 1969-02-19 | 1971-11-02 | United Aircraft Corp | Cast nickel-base alloy |
| US3655462A (en) * | 1971-03-22 | 1972-04-11 | United Aircraft Corp | Cast nickel-base alloy |
| US3904403A (en) * | 1972-12-14 | 1975-09-09 | Toyoda Chuo Kenkyusho Kk | Heat resisting nickel-aluminum-molybdenum alloy |
| US3933483A (en) * | 1972-07-14 | 1976-01-20 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Silicon-containing nickel-aluminum-molybdenum heat resisting alloy |
| US4006011A (en) * | 1972-09-27 | 1977-02-01 | Carpenter Technology Corporation | Controlled expansion alloy |
| US4012241A (en) * | 1975-04-22 | 1977-03-15 | United Technologies Corporation | Ductile eutectic superalloy for directional solidification |
| US4111723A (en) * | 1976-01-19 | 1978-09-05 | United Technologies Corporation | Directionally solidified eutectic superalloy articles |
| US4288259A (en) * | 1978-12-04 | 1981-09-08 | United Technologies Corporation | Tantalum modified gamma prime-alpha eutectic alloy |
| DE3242608A1 (en) * | 1981-11-27 | 1983-06-01 | United Technologies Corp., 06101 Hartford, Conn. | NICKEL-BASED SUPER ALLOY |
| FR2533232A1 (en) * | 1982-09-22 | 1984-03-23 | United Technologies Corp | HIGH-MODEL ELASTICITY ARTICLE |
| WO1986002719A1 (en) * | 1984-10-29 | 1986-05-09 | General Electric Company | Gun barrel for use at high temperature |
| US4740354A (en) * | 1985-04-17 | 1988-04-26 | Hitachi, Metals Ltd. | Nickel-base alloys for high-temperature forging dies usable in atmosphere |
| DE19926669A1 (en) * | 1999-06-08 | 2000-12-14 | Abb Alstom Power Ch Ag | Coating containing NiAl beta phase |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1277046A (en) * | 1918-02-23 | 1918-08-27 | Gen Alloys Company | Alloy. |
| GB127930A (en) * | 1918-04-10 | 1919-06-10 | Cooper Company | Improvements in Alloys. |
| FR698724A (en) * | 1929-10-11 | 1931-02-03 | Commentry Sa | Heat treatment process for alloys with high nickel and chromium content |
| US1803468A (en) * | 1930-07-03 | 1931-05-05 | Gilby Wire Company | Electrical-resistance alloy |
| US1924245A (en) * | 1930-07-04 | 1933-08-29 | Vereinigte Stahlwerke Ag | Process for improving nickel-molybdenum alloys |
| GB425614A (en) * | 1933-09-15 | 1935-03-15 | Henry Winder Brownsdon | Improvements in or relating to heat resisting alloys |
| US2071645A (en) * | 1933-12-29 | 1937-02-23 | Int Nickel Co | Electrode and electrical contact |
| GB583841A (en) * | 1941-12-17 | 1947-01-01 | Mond Nickel Co Ltd | Improvements relating to heat-resisting alloys |
| US2460590A (en) * | 1946-05-11 | 1949-02-01 | Driver Harris Co | Electric resistance element and method of heat-treatment |
-
1948
- 1948-07-19 US US39581A patent/US2542962A/en not_active Expired - Lifetime
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1277046A (en) * | 1918-02-23 | 1918-08-27 | Gen Alloys Company | Alloy. |
| GB127930A (en) * | 1918-04-10 | 1919-06-10 | Cooper Company | Improvements in Alloys. |
| FR698724A (en) * | 1929-10-11 | 1931-02-03 | Commentry Sa | Heat treatment process for alloys with high nickel and chromium content |
| US1803468A (en) * | 1930-07-03 | 1931-05-05 | Gilby Wire Company | Electrical-resistance alloy |
| US1924245A (en) * | 1930-07-04 | 1933-08-29 | Vereinigte Stahlwerke Ag | Process for improving nickel-molybdenum alloys |
| GB425614A (en) * | 1933-09-15 | 1935-03-15 | Henry Winder Brownsdon | Improvements in or relating to heat resisting alloys |
| US2071645A (en) * | 1933-12-29 | 1937-02-23 | Int Nickel Co | Electrode and electrical contact |
| GB583841A (en) * | 1941-12-17 | 1947-01-01 | Mond Nickel Co Ltd | Improvements relating to heat-resisting alloys |
| US2460590A (en) * | 1946-05-11 | 1949-02-01 | Driver Harris Co | Electric resistance element and method of heat-treatment |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3330633A (en) * | 1964-06-26 | 1967-07-11 | United Aircraft Corp | Coatings for high-temperature alloys |
| US3403996A (en) * | 1965-09-17 | 1968-10-01 | Matsushita Electric Industrial Co Ltd | Ferromagnetic material |
| US3429697A (en) * | 1967-03-30 | 1969-02-25 | Gen Electric | Process for producing cobalt-aluminum bodies |
| US3617397A (en) * | 1969-02-19 | 1971-11-02 | United Aircraft Corp | Cast nickel-base alloy |
| US3655462A (en) * | 1971-03-22 | 1972-04-11 | United Aircraft Corp | Cast nickel-base alloy |
| US3933483A (en) * | 1972-07-14 | 1976-01-20 | Kabushiki Kaisha Toyota Chuo Kenkyusho | Silicon-containing nickel-aluminum-molybdenum heat resisting alloy |
| US4006011A (en) * | 1972-09-27 | 1977-02-01 | Carpenter Technology Corporation | Controlled expansion alloy |
| US3904403A (en) * | 1972-12-14 | 1975-09-09 | Toyoda Chuo Kenkyusho Kk | Heat resisting nickel-aluminum-molybdenum alloy |
| US4012241A (en) * | 1975-04-22 | 1977-03-15 | United Technologies Corporation | Ductile eutectic superalloy for directional solidification |
| US4111723A (en) * | 1976-01-19 | 1978-09-05 | United Technologies Corporation | Directionally solidified eutectic superalloy articles |
| US4288259A (en) * | 1978-12-04 | 1981-09-08 | United Technologies Corporation | Tantalum modified gamma prime-alpha eutectic alloy |
| DE3242608A1 (en) * | 1981-11-27 | 1983-06-01 | United Technologies Corp., 06101 Hartford, Conn. | NICKEL-BASED SUPER ALLOY |
| FR2533232A1 (en) * | 1982-09-22 | 1984-03-23 | United Technologies Corp | HIGH-MODEL ELASTICITY ARTICLE |
| WO1986002719A1 (en) * | 1984-10-29 | 1986-05-09 | General Electric Company | Gun barrel for use at high temperature |
| US4669212A (en) * | 1984-10-29 | 1987-06-02 | General Electric Company | Gun barrel for use at high temperature |
| JPH068720B2 (en) * | 1984-10-29 | 1994-02-02 | ゼネラル・エレクトリック・カンパニイ | Barrel for use under high temperature and manufacturing method thereof |
| US4740354A (en) * | 1985-04-17 | 1988-04-26 | Hitachi, Metals Ltd. | Nickel-base alloys for high-temperature forging dies usable in atmosphere |
| DE19926669A1 (en) * | 1999-06-08 | 2000-12-14 | Abb Alstom Power Ch Ag | Coating containing NiAl beta phase |
| US6471791B1 (en) | 1999-06-08 | 2002-10-29 | Alstom (Switzerland) Ltd | Coating containing NiAl-β phase |
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