US3617263A - Corrosion-resistant nickel-chromium base alloy - Google Patents
Corrosion-resistant nickel-chromium base alloy Download PDFInfo
- Publication number
- US3617263A US3617263A US830848A US3617263DA US3617263A US 3617263 A US3617263 A US 3617263A US 830848 A US830848 A US 830848A US 3617263D A US3617263D A US 3617263DA US 3617263 A US3617263 A US 3617263A
- Authority
- US
- United States
- Prior art keywords
- percent
- alloy
- accordance
- titanium
- 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.)
- Expired - Lifetime
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 66
- 239000000956 alloy Substances 0.000 title claims abstract description 66
- 229910018487 Ni—Cr Inorganic materials 0.000 title abstract description 4
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 title abstract description 4
- 230000007797 corrosion Effects 0.000 title description 11
- 238000005260 corrosion Methods 0.000 title description 11
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 25
- 239000010936 titanium Substances 0.000 claims abstract description 25
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 24
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 24
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 24
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 24
- 239000010955 niobium Substances 0.000 claims abstract description 24
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims abstract description 23
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 22
- 239000011651 chromium Substances 0.000 claims abstract description 20
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 18
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052761 rare earth metal Inorganic materials 0.000 claims abstract description 12
- 150000002910 rare earth metals Chemical class 0.000 claims abstract description 12
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 12
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims abstract description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 11
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 11
- 239000010941 cobalt Substances 0.000 claims abstract description 11
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 11
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 10
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052796 boron Inorganic materials 0.000 claims abstract description 10
- 229910052726 zirconium Inorganic materials 0.000 claims abstract description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 230000002596 correlated effect Effects 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 description 14
- 238000012360 testing method Methods 0.000 description 14
- 230000032683 aging Effects 0.000 description 7
- 230000035882 stress Effects 0.000 description 5
- 239000000470 constituent Substances 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 239000012535 impurity Substances 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 230000002035 prolonged effect Effects 0.000 description 4
- HEMHJVSKTPXQMS-UHFFFAOYSA-M Sodium hydroxide Chemical compound [OH-].[Na+] HEMHJVSKTPXQMS-UHFFFAOYSA-M 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 150000003839 salts Chemical class 0.000 description 3
- 239000004215 Carbon black (E152) Substances 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 2
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 229930195733 hydrocarbon Natural products 0.000 description 2
- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910052750 molybdenum Inorganic materials 0.000 description 2
- 239000011733 molybdenum Substances 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 239000011833 salt mixture Substances 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- 239000010703 silicon Substances 0.000 description 2
- 229910052715 tantalum Inorganic materials 0.000 description 2
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 2
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- 229910001122 Mischmetal Inorganic materials 0.000 description 1
- 229910020018 Nb Zr Inorganic materials 0.000 description 1
- PMZURENOXWZQFD-UHFFFAOYSA-L Sodium Sulfate Chemical compound [Na+].[Na+].[O-]S([O-])(=O)=O PMZURENOXWZQFD-UHFFFAOYSA-L 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000002939 deleterious effect Effects 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000037406 food intake Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000011780 sodium chloride Substances 0.000 description 1
- 229910052938 sodium sulfate Inorganic materials 0.000 description 1
- 235000011152 sodium sulphate Nutrition 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000004580 weight loss Effects 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
- C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
Definitions
- ABSTRACT A nickel-chromium base alloy adapted for turbine blade manufacture contains, in addition to nickel and chromium, cobalt and correlated amounts of niobium, titanium and aluminum, as well as carbon and boron. Other elements such as zirconium, rare earth metal and yttrium can be present.
- the alloys contemplated in accordance herewith contain (by weight) at least 27 percent chromium for good high-temperature corrosion resistance but not more than about 31 percent in order to avoid risking undue embrittlement.
- the chromium content is from 28 percent to 29.5 percenLFrom 10 to 25 percent cobalt strengthens the alloys, and it is to advantage that from 15 to 22 percent cobalt is present.
- the alloys are further strengthened by the copresence of niobium, titanium and aluminum. in this connection, stressrupture strength falls off markedly at niobium contents less than 0.2 percent and beneficially the niobium content is from 0.3 to 1.5 percent.
- niobium More than 2 percent niobium leads to embrittlement and loss of impact strength, and also to loss of stress-rupture strength and ductility.
- Teantalum may be introduced incidentally with the niobium in an amount up to about one-tenth of the niobium content. For the purposes of the present invention, such amounts of tantalum are to be regarded as part of the niobium content.
- the sum of the titanium and aluminum contents must be from 2.25 to 4.5 percent, for either above or below these limits the stress-rupture strength falls off, and too much titanium and aluminum also renders the alloys susceptible to embrittlement on prolonged heating at high temperatures.
- the sum of these constituents is from 3 to 4 percent.
- stress-rupture strength also depends on the ratio of titanium to aluminum, and this. must be from 1:1 to 4:1, and is preferably from 1.521 to 2.521. The best combination of strength and elongation in stress-rupture tests is shown by alloys in which this ratio is about 2: l.
- Carbon is also of importance. If it is too low, stress-rupture strength is reduced, while if to the excess the alleys become susceptible to embrittlement. Hence, the carbon content should be from 0,2 to 0.1 percent, and is preferably from 0.04 to 0.08 percent.
- zirconium both improve the stress-rupture strength of the alloys, and they must contain at least 0.002 but not more than 0.01 percent boron.
- Zirconium may be present in, amounts up to 0.6 percent but no particular advantage is found in using more than 0.1 percent.
- the resistance of the alloys to oxidation and scaling is improved by the presence of rare earth metals, and one or more of these metals may be added, for example, in the form of misch metal.
- rare earth metals e.g., from about 0.03 to 0.08 percent.
- Yttrium too improves oxidation and scaling resistance and also resistance to sulphidation. Accordingly, yttrium may advantageously be added in amounts from 0.2 to 2 percent, for example, from 0,5 to 1 percent.
- silicon has a deleterious effect on corrosion resistance and should therefore be kept below 1 percent and preferably below 0.5 percent.
- Other impurities may include manganese in amounts up to 1 percent and iron in amounts up to 2 percent.
- the solution treatment may comprise heating from 1 to 8 hours in the temperature range of 1,050 to 1,200 C., and the alloys may then be aged by heating for 1 to 24 hours in the temperature range of 800 to 950 C.
- An intermediate aging treatment consisting of heating for l to 16 hours at 800 to l,050 C. may be interposed between the solution treatment and the final aging stages.
- alloys may be cooled at any convenient rate after each heat treatment stage, e.g., by air-cooling (generally to As will be seen from results in table II, alloy D, which contained too little titanium and aluminum, had a low stress-rupture life in comparison with alloys 1 and 2 according to the invention. Alloy 5, which contained too much niobium and had room temperature) or by direct transfer from a furnace at one 5 an A Factor greater than 40, had very low impact strength temperature to one at a lower temperature. after prolonged heating at 850 C. In marked contrast, alloy 3,
- alloys within the invention alloys 1-3, table I, 10 and although it had good stress-rupture life, its A" Factor were tested in the form of specimens machined from forged was greater than 40 and its impact strength was low. lts stressbar that had been heat treated by solution heating for 4 hours rupture elongation was also rather low. Alloy F is an example at l,l50 C., air-cooling, aging for 16 hours at l,050 C., airof an alloy which is excluded from the invention only because cooling and finally aging for 16 hours at 850 C. and again airthe contents of niobium, titanium, aluminum and chromium cooling. For purposes of comparison, there is included some 15 are not interrelated as required by the invention.
- test A samples of each alloy loys 3, F and G were aged in a single stage by heating for 16 were half immersed in the salt mixture while heated in air hours at 850 C. and air-cooled. The tests were then perwhereas in test B samples of each alloy were heated in a vertiformed under the same conditions as those in table I, but the 4 cal open-top furnace into which the salt mixture was continuspecimens used for the impact tests (Charpy V-notch were ously fed as a fine dispersion at a rate of5 g./hour.
- alloy H which is a commercially available alloy of comparable stress-rupture strength but lower chromium content.
- the alloys can be air melted, but to ensure the best creep properties they are preferably melted and cast under vacuum. They can be readily processed by conventional means such as extrusion, forging, or rolling. Although primarily intended for use in the wrought form as gas turbine blades, the subject alloys are suitable for use in other applications where a combination of good stress-rupture strength and resistance to corrosion is required, particularly for articles ad parts that are subjected in use to stress at high temperatures while exposed to the combustion products of impure hydrocarbon fuels or to salt or both. They may also be used to make cast articles and parts, which may be used with or without heat treatment.
- balance or balance essentially usedin referring to the nickel content does not exclude the presence of small amounts of other elements, commonly present as incidental elements, e.g., deoxidizing and cleansing constituents, and impurities ordinarily associated therewith in small amounts which do no adversely affect the basic characteristics of the alloys.
- An alloy consisting of about 27 to about 31 percent chromium, about to 25 percent cobalt, from 0.2 to 2 percent niobium, about 2.25 to about 4.5 percent total of titanium and aluminum with the provisos that (a) the ratio of titanium to aluminum is from about 1:1 to about 4:1 and (b) the much lower stress-rupture strength and greatly superior to V value of the A Factor as determined by the relationship 5(%Nb)+4(%Ti+Al)+c/(%Cr) does not exceed about 40, about 0.02 to 0.1 percent carbon, about 0.002 to 0.01 percent boron, up to 0.6 percent zirconium, up to about 0.3 percent of rare earth metal, up to 2 percent yttrium and the balance essentially nickel.
- An alloy in accordance with claim 1 containing about 3 to 4 percent total of titanium plus aluminum.
- An alloy in accordance with claim 1 containing about 0.04 to 0.8 percent carbon.
- An alloy in accordance with claim 1 containing about 0.01 to 0.3 percent rare earth metal.
- An alloy in accordance with claim 1 containing about 0.2 to 2 percent yttrium.
- An alloy in accordance with claim 1 containing about 0.5 to 1 percent yttrium.
- An alloy in accordance with claim 1 containing about 28 to about 29 percent chromium, about 19 to about 21 percent cobalt, about 0.5 to about 1 percent niobium, about 2.1 to about 2.5 percent titanium, about 1.1 to about 1.4 percent aluminum, about 0.04 to about 0.06 percent carbon, about 0.002 to about 0.01 percent boron, about 0.04 to about 0.1 percent zirconium, up to about 0.3 percent rare earth metal, up to about 1 percent yttrium, and the balance essentially nickel.
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)
- Manufacture And Refinement Of Metals (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB27671/68A GB1199240A (en) | 1968-06-11 | 1968-06-11 | Improvements relating to Nickel-Chromium Alloys |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3617263A true US3617263A (en) | 1971-11-02 |
Family
ID=10263382
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US830848A Expired - Lifetime US3617263A (en) | 1968-06-11 | 1969-06-05 | Corrosion-resistant nickel-chromium base alloy |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US3617263A (de) |
| AT (1) | AT288041B (de) |
| BE (1) | BE734417A (de) |
| CH (1) | CH505904A (de) |
| FR (1) | FR2010696A1 (de) |
| GB (1) | GB1199240A (de) |
| NL (1) | NL140292B (de) |
| SE (1) | SE359572B (de) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4056389A (en) * | 1971-05-20 | 1977-11-01 | The International Nickel Company, Inc. | Nickel-chromium high strength casting |
| US5330710A (en) * | 1989-01-09 | 1994-07-19 | Doryokuro Kakunenryo Kaihatsu Jigyodan | Nickel-base alloy for glass-contracting member used in unenergized state |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10219377A (ja) * | 1997-02-07 | 1998-08-18 | Daido Steel Co Ltd | ディーゼルエンジンの高耐食性吸排気バルブ用合金及び吸排気バルブの製造方法 |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3408179A (en) * | 1964-08-14 | 1968-10-29 | Int Nickel Co | Corrosion-resistant nickel-chromium alloys with improved stress-rupture characteristics |
| US3466171A (en) * | 1965-07-20 | 1969-09-09 | Int Nickel Co | Nickel-chromium-niobium alloy |
-
1968
- 1968-06-11 GB GB27671/68A patent/GB1199240A/en not_active Expired
-
1969
- 1969-06-05 US US830848A patent/US3617263A/en not_active Expired - Lifetime
- 1969-06-10 CH CH881369A patent/CH505904A/fr not_active IP Right Cessation
- 1969-06-10 AT AT550569A patent/AT288041B/de not_active IP Right Cessation
- 1969-06-10 SE SE08231/69A patent/SE359572B/xx unknown
- 1969-06-10 NL NL696908846A patent/NL140292B/xx unknown
- 1969-06-11 FR FR6919413A patent/FR2010696A1/fr not_active Withdrawn
- 1969-06-11 BE BE734417D patent/BE734417A/xx unknown
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3408179A (en) * | 1964-08-14 | 1968-10-29 | Int Nickel Co | Corrosion-resistant nickel-chromium alloys with improved stress-rupture characteristics |
| US3466171A (en) * | 1965-07-20 | 1969-09-09 | Int Nickel Co | Nickel-chromium-niobium alloy |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4056389A (en) * | 1971-05-20 | 1977-11-01 | The International Nickel Company, Inc. | Nickel-chromium high strength casting |
| US5330710A (en) * | 1989-01-09 | 1994-07-19 | Doryokuro Kakunenryo Kaihatsu Jigyodan | Nickel-base alloy for glass-contracting member used in unenergized state |
Also Published As
| Publication number | Publication date |
|---|---|
| SE359572B (de) | 1973-09-03 |
| NL140292B (nl) | 1973-11-15 |
| BE734417A (de) | 1969-12-11 |
| DE1929301A1 (de) | 1970-08-27 |
| NL6908846A (de) | 1969-12-15 |
| FR2010696A1 (de) | 1970-02-20 |
| DE1929301B2 (de) | 1977-03-03 |
| CH505904A (fr) | 1971-04-15 |
| AT288041B (de) | 1971-02-25 |
| GB1199240A (en) | 1970-07-15 |
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