US2975051A - Nickel base alloy - Google Patents
Nickel base alloy Download PDFInfo
- Publication number
- US2975051A US2975051A US843056A US84305659A US2975051A US 2975051 A US2975051 A US 2975051A US 843056 A US843056 A US 843056A US 84305659 A US84305659 A US 84305659A US 2975051 A US2975051 A US 2975051A
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- US
- United States
- Prior art keywords
- nickel base
- alloy
- tungsten
- molybdenum
- alloys
- 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.)
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims description 45
- 239000000956 alloy Substances 0.000 title claims description 39
- 229910045601 alloy Inorganic materials 0.000 title claims description 39
- 229910052759 nickel Inorganic materials 0.000 title claims description 22
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 19
- 229910052721 tungsten Inorganic materials 0.000 claims description 18
- 229910052750 molybdenum Inorganic materials 0.000 claims description 17
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 17
- 239000010937 tungsten Substances 0.000 claims description 17
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 16
- 239000011733 molybdenum Substances 0.000 claims description 16
- 229910052782 aluminium Inorganic materials 0.000 claims description 11
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 11
- 239000010936 titanium Substances 0.000 claims description 11
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 10
- 229910052719 titanium Inorganic materials 0.000 claims description 10
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 9
- 229910052796 boron Inorganic materials 0.000 claims description 9
- 239000011651 chromium Substances 0.000 claims description 9
- 229910052742 iron Inorganic materials 0.000 claims description 9
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 8
- 229910052799 carbon Inorganic materials 0.000 claims description 8
- 229910052804 chromium Inorganic materials 0.000 claims description 8
- 239000012535 impurity Substances 0.000 claims description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 7
- 238000005266 casting Methods 0.000 claims description 7
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 5
- 229910052726 zirconium Inorganic materials 0.000 claims description 5
- 238000012360 testing method Methods 0.000 description 6
- 238000001816 cooling Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 3
- 230000006698 induction Effects 0.000 description 2
- 239000011572 manganese Substances 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
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000000243 solution Substances 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
- C22C19/056—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%
Definitions
- This invention relates to nickel base alloys particularly useful at elevated temperatures in cast form and, more particularly, to such alloys including chromium, aluminum, titanium, molybdenum, boron and tungsten.
- a principal object of this invention is to provide an alloy suitable for casting which has high strength and ductility for practical use at about 2100 F. Another object is to provide a nickel base alloy including a relatively critical range of such elements as boron, iron, aluminum titanium, molybdenum and tungsten in order to assure sufiicient strength and ductility in an article for elevated temperature operation.
- a further object is to provide a nickel base alloy having a balance of molybdenum and tungsten which results in an alloy of unusual stress rupture life.
- this invention in one form provides a nickel base castable alloy comprising in percent by weight up to about 0.08 carbon, 0-6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 1.4-4.1 tungsten, 0-0.1 zirconium with the balance essentially nickel, impurities and the usual small amounts of silicon and manganese normally found in this type of alloy.
- the elements aluminum, titanium and molybdenum have been combined in various amounts to produce precipitated phases or solid solutions in order to strengthen andl harden high temperature nickel base alloys.
- tungsten has been included in some nickel base alloys as an alloying eternent, usually tungsten and molybdenum have not been components of the same nickel base alloy along with the elements aluminum and titanium.
- this invention it has been found that the inclusion of all such elements within a relatively narrow range of composition and the low iron content in some forms results in an alloy having unexpectedly high stress rupture strength along with good tensile ductility especially in the 2000-2150" F. operation range.
- the alloy of this invention has the strength of a cast alloy and an unusual high tensile ductility generally found only in wrought alloys. Such properties expand the possible uses of the alloy of this invention over those of other cast alloys to include applications 2 under high impact and stress conditions by insuring better stress distribution.
- compositions of Table I Initial studies of the inter-relationship of aluminum; molybdenum and tungsten in nickel base alloys in connection with this invention are represented by the compositions of Table I.
- UT means Strength, the value in pounds per square inch obtained when the maximum load recorded during the straining of a specimen is divided by the cross-sectional area of the specimen before straining; El, which means Tensile Elongation, is the amount of permanent extension in the fracture area in a tension test and is a measure of the permanent deformation before fracture by stress in tension; RA which means Reductionin Area? is another I measure of the ductility of an alloy; and Rupture Life.”
- Alloys B, C and F have been shown to have unusual stress rupture life and tensile ductility as shown by the comparison of data in Tables IV and V below.
- the alloys from which representative examples are shown in tables herein were prepared by induction vacuum melting and vacuum induction investment casting to specified grain sizes for control of testing. Grain sizes were measured at the face of the ingot adjacent the test bar section.
- a nickel base alloy suitable for casting comprising in percent by weight up to about 0.08 carbon, up to 6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 1.4-4.1 tungsten, up to 0.1 zirconium, with the balance essentially nickel and impurities.
- a nickel base alloy suitable for casting comprising in percent by weight up to about 0.08 carbon, 4-6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 2.0-2.5 tungsten, with the balance essentially nickel and impurities.
- a nickel base alloy suitable for casting comprising in percent by weight up to about 0.08 carbon, 4-6 iron, 0.070.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 3.5-4.0 tungsten, with the balance essentially nickel and impurities.
- a nickel base alloy suitable for casting comprising in percent by weight up to about 0.04 carbon, up to about 0.2 iron, 0.07-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 2.5- 3.0 tungsten, 0.05-0.10 zirconium, with the balance essentially nickel and impurities.
- a nickel base alloy suitable for casting comprising in percent by Weight up to about 0.08 carbon; up to 6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 1.4-4.1 tungsten, up to 0.1 zirconium, with the balance essentially nickel and impurities, the sum of the weight percentages of molybdenum and one-half of tungsten being 4-6.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Powder Metallurgy (AREA)
Description
United States Patent 2,e7s,051' v NICKEL BASE ALLOY James E. Wilson, Loveland, and Eugene L. Dunn, Ba-
tavia, Ohio, assignors to General Electric Company, a corporation of New York No Drawing. Filed Sept. 29, 1959, Ser. No.- 843,056
Claims. (Cl. 75-171) This invention relates to nickel base alloys particularly useful at elevated temperatures in cast form and, more particularly, to such alloys including chromium, aluminum, titanium, molybdenum, boron and tungsten.
. Following the advance of technology in the field of clude those of good tensile ductility along with adequate life under stress conditions at temperatures of about 2000 F. or above.
A principal object of this invention is to provide an alloy suitable for casting which has high strength and ductility for practical use at about 2100 F. Another object is to provide a nickel base alloy including a relatively critical range of such elements as boron, iron, aluminum titanium, molybdenum and tungsten in order to assure sufiicient strength and ductility in an article for elevated temperature operation.
A further object is to provide a nickel base alloy having a balance of molybdenum and tungsten which results in an alloy of unusual stress rupture life.
These and other objects and advantages of this invention will be more readily understood when viewed in connection with the following more detailed description. The scope of the invention will be'pointed out in the appended claims.
Briefly stated, this invention in one form provides a nickel base castable alloy comprising in percent by weight up to about 0.08 carbon, 0-6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 1.4-4.1 tungsten, 0-0.1 zirconium with the balance essentially nickel, impurities and the usual small amounts of silicon and manganese normally found in this type of alloy.
The elements aluminum, titanium and molybdenum have been combined in various amounts to produce precipitated phases or solid solutions in order to strengthen andl harden high temperature nickel base alloys. Although tungsten has been included in some nickel base alloys as an alloying elernent, usually tungsten and molybdenum have not been components of the same nickel base alloy along with the elements aluminum and titanium. Through this invention it has been found that the inclusion of all such elements within a relatively narrow range of composition and the low iron content in some forms results in an alloy having unexpectedly high stress rupture strength along with good tensile ductility especially in the 2000-2150" F. operation range.
In its cast form, the alloy of this invention has the strength of a cast alloy and an unusual high tensile ductility generally found only in wrought alloys. Such properties expand the possible uses of the alloy of this invention over those of other cast alloys to include applications 2 under high impact and stress conditions by insuring better stress distribution.
Initial studies of the inter-relationship of aluminum; molybdenum and tungsten in nickel base alloys in connection with this invention are represented by the compositions of Table I. The composition of the alloys shown included in addition to the elements of Table I, in percent by weight up to 0.08 C, 3.5-6 Fe, 0.07-0.09 B, 14-16 Cr, 3.25-3.75 Ti, amaximum of 0.01 Mn, a maximum of 0.03 Si, with the balance essentially Ni and impurities.
TABLE I Elements (percent by weight) Alloy I v Al "Mo W It can be seen in Table II that the tensile ductility and stress rupture lives of alloys W-2 and W-3 were very much gerater than the other W series alloys of approximately the same ultimate tensile strengths. The test bars which were used to obtain the values in Table II were standard 0.160 inch diameter, one inch gauge length bars.
TABLE II Alloy RA, Percent UTS, 1,000 p.s.i.
- El, Percent The alloys of Table I were heat treated by heating first to 2100 F. for one hour, air cooling, heating to 1950 F. for two hours, air cooling, heating to-1550 Eliot four hours and then air cooling prior to testing the results of which are shown in Table II.
As used herein UT means Strength, the value in pounds per square inch obtained when the maximum load recorded during the straining of a specimen is divided by the cross-sectional area of the specimen before straining; El, which means Tensile Elongation, is the amount of permanent extension in the fracture area in a tension test and is a measure of the permanent deformation before fracture by stress in tension; RA which means Reductionin Area? is another I measure of the ductility of an alloy; and Rupture Life."
is a measure of the length of time an alloy resists failure at a given stressand temperature.
By comparing W-2 with W-6, it is to .be noted that molybdenum and tungsten are not interchangeable in this alloy nor do they have the same results on the mechanical Patented Mar. 14, 1961 0 Ultimate Tensile TABLE III Alloys (percent by weight) Elements B O D F G H T 08 max 08 max. 04 max. 04 max. .04 max. 12
4 4-6 2 max. .2 max. .2 max. 07-. 05-. 10 07-. 10 07-. 10 07-. 10 05-. 10 14-16 14-17 1 1-16 14-10 14-10 12-14 4. 3-. 0 3. 6-5 4. 3-5. 0 5. 5-6. 5 5. 5-0. 5 5 5-6. 3. 2" 3. 75 3-4 3. 25-3. 75 .3-1 .3-1 .3-1 3. 5-4. 0 4-7 3. 5-4. 0 3. 5-4. 0 3. 5-4. 0 0 3. 5-1. 0 0 2. 5-3. 0 2. 5-3. 0 2. 5-3. 0 8-10 0 0 .05-. 10 05-. 10 .05- 10 .05-. 10 0 0 0 0 1. 5-2. 5 1-3 Bal. Bal. 13:11. 13211. Bal. Bal.
Alloys B, C and F have been shown to have unusual stress rupture life and tensile ductility as shown by the comparison of data in Tables IV and V below.
TABLE IV Stress rupture life (like grain size) Temp. Stress Liie Alloy F.) (1,000 (hrs) p.s.i.)
e =r a 1,850 15.0 245 1, 850 15.0 196 TABLE V Tensile reduction in area [Percent 1,300 F.]
Grain Size Alloy y, 2 r! %!l 2/! From a study of the compositions of the above listed alloys and their resulting rupture lives, it has been recognized that molybdenum and tungsten complement each other. This invention recognizes that in percent by weight and times the Mo content added to one-half times the tungsten content lies in the range of about 4-6. Thus,
numerically the W and Mo being weight percents.
Prior to the testing of the specimens the data for which is shown in Tables IV and V, the specimens were solution heat treated at about 2100 F. for one hour before air cooling.
The alloys from which representative examples are shown in tables herein were prepared by induction vacuum melting and vacuum induction investment casting to specified grain sizes for control of testing. Grain sizes were measured at the face of the ingot adjacent the test bar section.
Although this invention has been described in connection with specific examples, it will be understood by those skilled in the art of metallurgy the modifications and variations of which this invention is capable.
What is claimed is:
1. A nickel base alloy suitable for casting comprising in percent by weight up to about 0.08 carbon, up to 6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 1.4-4.1 tungsten, up to 0.1 zirconium, with the balance essentially nickel and impurities.
2. A nickel base alloy suitable for casting comprising in percent by weight up to about 0.08 carbon, 4-6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 2.0-2.5 tungsten, with the balance essentially nickel and impurities.
3. A nickel base alloy suitable for casting comprising in percent by weight up to about 0.08 carbon, 4-6 iron, 0.070.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 3.5-4.0 tungsten, with the balance essentially nickel and impurities.
4.. A nickel base alloy suitable for casting comprising in percent by weight up to about 0.04 carbon, up to about 0.2 iron, 0.07-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 2.5- 3.0 tungsten, 0.05-0.10 zirconium, with the balance essentially nickel and impurities.
5. A nickel base alloy suitable for casting comprising in percent by Weight up to about 0.08 carbon; up to 6 iron, 0.05-0.10 boron, 14-16 chromium, 4.3-5.0 aluminum, 3.25-3.75 titanium, 3.5-4.0 molybdenum, 1.4-4.1 tungsten, up to 0.1 zirconium, with the balance essentially nickel and impurities, the sum of the weight percentages of molybdenum and one-half of tungsten being 4-6.
References Cited in the file of this patent UNITED STATES PATENTS
Claims (1)
1. A NICKEL BASE ALLOY SUITABLE FOR CASTING COMPRISING IN PERCENT BY WEIGHT UP TO ABOUT 0.08 CARBON, UP TO 6 IRON, 0.05-0.10 BORON, 14-16 CHROMIUM, 4.3-5.0 ALUMINUM, 3.25-3.75 TITANIUM, 3.5-4.0 MOLYBDENUM, 1.4-4.1 TUNGSTEN, UP TO 0.1 ZIRCONIUM, WITH THE BALANCE ESSENTIALLY NICKEL AND IMPURITIES.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US843056A US2975051A (en) | 1959-09-29 | 1959-09-29 | Nickel base alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US843056A US2975051A (en) | 1959-09-29 | 1959-09-29 | Nickel base alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2975051A true US2975051A (en) | 1961-03-14 |
Family
ID=25288965
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US843056A Expired - Lifetime US2975051A (en) | 1959-09-29 | 1959-09-29 | Nickel base alloy |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2975051A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3166412A (en) * | 1962-08-31 | 1965-01-19 | Int Nickel Co | Cast nickel-base alloy for gas turbine rotors |
| US3293030A (en) * | 1962-05-12 | 1966-12-20 | Birmingham Small Arms Co Ltd | Nickel-base alloys |
| US3385698A (en) * | 1965-04-09 | 1968-05-28 | Carpenter Steel Co | Nickel base alloy |
| US3467516A (en) * | 1966-05-02 | 1969-09-16 | Gen Electric | Wrought nickel base alloy |
| USRE28681E (en) * | 1973-04-02 | 1976-01-13 | High temperature alloys | |
| USRE29920E (en) * | 1975-07-29 | 1979-02-27 | High temperature alloys | |
| EP0068628A2 (en) * | 1981-06-12 | 1983-01-05 | Special Metals Corporation | Castable nickel base alloy |
| US4530727A (en) * | 1982-02-24 | 1985-07-23 | The United States Of America As Represented By The Department Of Energy | Method for fabricating wrought components for high-temperature gas-cooled reactors and product |
| US4629521A (en) * | 1984-12-10 | 1986-12-16 | Special Metals Corporation | Nickel base alloy |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2766155A (en) * | 1952-12-02 | 1956-10-09 | Int Nickel Co | Production of high temperature articles and alloys therefor |
| GB769822A (en) * | 1954-06-28 | 1957-03-13 | Gen Motors Corp | Improvements in nickel-base alloys |
-
1959
- 1959-09-29 US US843056A patent/US2975051A/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2766155A (en) * | 1952-12-02 | 1956-10-09 | Int Nickel Co | Production of high temperature articles and alloys therefor |
| GB769822A (en) * | 1954-06-28 | 1957-03-13 | Gen Motors Corp | Improvements in nickel-base alloys |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3293030A (en) * | 1962-05-12 | 1966-12-20 | Birmingham Small Arms Co Ltd | Nickel-base alloys |
| US3166412A (en) * | 1962-08-31 | 1965-01-19 | Int Nickel Co | Cast nickel-base alloy for gas turbine rotors |
| US3385698A (en) * | 1965-04-09 | 1968-05-28 | Carpenter Steel Co | Nickel base alloy |
| US3467516A (en) * | 1966-05-02 | 1969-09-16 | Gen Electric | Wrought nickel base alloy |
| USRE28681E (en) * | 1973-04-02 | 1976-01-13 | High temperature alloys | |
| USRE29920E (en) * | 1975-07-29 | 1979-02-27 | High temperature alloys | |
| EP0068628A2 (en) * | 1981-06-12 | 1983-01-05 | Special Metals Corporation | Castable nickel base alloy |
| EP0068628A3 (en) * | 1981-06-12 | 1983-02-02 | Special Metals Corporation | Castable nickel base alloy |
| US4530727A (en) * | 1982-02-24 | 1985-07-23 | The United States Of America As Represented By The Department Of Energy | Method for fabricating wrought components for high-temperature gas-cooled reactors and product |
| US4629521A (en) * | 1984-12-10 | 1986-12-16 | Special Metals Corporation | Nickel base alloy |
| AU574538B2 (en) * | 1984-12-10 | 1988-07-07 | Societe National D'etude Et De Construction De Moteurs D'aviation | Nickel & chromium base mo,w,co,al,ti,b,zr alloy |
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