US3457066A - Nickel base alloy - Google Patents

Nickel base alloy Download PDF

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Publication number
US3457066A
US3457066A US806204A US3457066DA US3457066A US 3457066 A US3457066 A US 3457066A US 806204 A US806204 A US 806204A US 3457066D A US3457066D A US 3457066DA US 3457066 A US3457066 A US 3457066A
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United States
Prior art keywords
alloy
nickel base
strength
base alloy
stress
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Expired - Lifetime
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US806204A
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English (en)
Inventor
Marvin A Pohlman
Joseph B Moore
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General Electric Co
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General Electric Co
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    • 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

  • Nickel base alloys including relatively wide ranges of cobalt, chromium, molybdenum, titanium and aluminum as their principle alloying elements have been reported as suitable for high temperature use under Conditions ofrelatively high stress. However, the unexpected advantages of a close balance between certain of these elements in narrower ranges had not been completely explored.
  • Another object is to provide ⁇ a vacuum melted nickel base alloy which in sheet form exceeds the tensile and rupture strengths of known sheet alloys at elevated ternperatures.
  • our alloy we provide a nickel base sheet alloy comprising in percent by weight Aup to about 0.08 carbon, about 14-17 chromium, about .0.01-
  • FIG. 3 is a graph of the 0.2 percent yield strength and i' of our alloy in its broad range.
  • Stress rupture strength is the value of stress in pounds per square inch obtained by dividing the amount of an applied load by the area supporting that load initially while the test speciman is maintained at a selected temperature.
  • the strength of material of a test specimen is also to failure under a specied stress and at a specified tem- Ultimate tensile strength is the value in pounds per squareinch obtained when the maximum load recorded during the plastic straining of a specimen is divided by p the cross sectional area of the specimen before straining.
  • Our sheet alloy in its lower range ofcobalt after a heat treatment such as heating at' about 2100 F. for about one half hour, air cooling,lheati'r'1 ⁇ g at about 1400" FL for about sixteen (16) hours 'and then air cooling," is characterized by particularly high elevated. temperaturertensile strength; in its upper range of 'cobalt it has exceptionally high elevated temperature stress rupture strength after that same type of heat treatment.
  • FIG. l is a graph of the average stress rupture life of our preferred sheet alloy compared with the strongest of other available sheet alloys;
  • FIG. 2 is a graph of the ultimate tensile strength band of our alloy in its broad range
  • 0.2% vyield strength shown in FIG. 3 is the stress at which a material exhibits 0.2% deviation from the proportionality of stress to strain. This figure, sometimes referred to as 0.2% offset is commonly used as the basis of design strength of articles.
  • the stress rupture strengths of the alloys after heat treatment are represented by the comparison of stress with a time-temperature parameter shown at the horizontal coordinate.
  • the curves of FIG. l have been prepared from a large amount of stress rupture test results and represent a compact summary of a wide range of data. Using this special graph, it is possible to predict the stress rupture life of a material under a given load at a given temperature.
  • the curves of FIG. 1 show that the stress rupture strength of our vacuum melted sheet alloy in its preferred range is greater than that of the two strongest sheet alloys available, each after heat treatment.
  • EXAMPLE 1 TABLE II Stress rupture lite Temperature F.) Stress (1,000 p.s.i.) (hours) A Series of sheet materials of the compositions shown in Table III were to a thickness of about 0.065 inch and heat treated as in Example 1. The compositions are 1n percent by weight.
  • 1.'A wrought nickel base alloy consisting of in percent by weight about 0.04-0.07 carbon, about 14.5-15.5 chromium, about 0025-0035 boron about 14.5-15.5 cobalt, about 4'.5-5.5 molybdenum, about 3.3-3.7 titanium, about 4.2-4.6 aluminum, with the balance nickel and impurities.
  • the alloy of claim 1 consisting in additions in percent by weight up to about 0.1 silicon and up to about 0.1 manganese.
  • a wrought nickel base alloy consisting of in percent by weight about 0.06 carbon, about l5 chromium, about 0.03 boron, about 15 cobalt, about 5 molybdenum, about 3.5 titanium, about 4.5 aluminum, with the balance nickel and impurities.
  • a nickel base alloy consisting of in percent -by weight, 14.5-l5.5 chromium, l4.5-l5.5 cobalt, 3.3-3.7 titanium, 4.2-4.5 alumium, .025-.035 boron, 4.5-5.5 molybdenum vand the balance nickel.
  • a nickel base alloy consisting essentially of from 14.0% to 17.0% chromium, from 13.0% to 20.0% cobalt, from 3.25% to 3.75% titanium, from 4.0% to 4.5% aluminum, from 0.02% to 0.04% boron and from 4.50% to 5.50% molybdenum, the balance Ibeing essentially all nickel.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Continuous Casting (AREA)
  • Manufacture And Refinement Of Metals (AREA)
US806204A 1959-04-10 1959-04-10 Nickel base alloy Expired - Lifetime US3457066A (en)

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US80620459A 1959-04-10 1959-04-10

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US3457066A true US3457066A (en) 1969-07-22

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US (1) US3457066A (de)
BE (1) BE589397A (de)
CH (1) CH398979A (de)
GB (1) GB893617A (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4957567A (en) * 1988-12-13 1990-09-18 General Electric Company Fatigue crack growth resistant nickel-base article and alloy and method for making
US5080734A (en) * 1989-10-04 1992-01-14 General Electric Company High strength fatigue crack-resistant alloy article
US5413752A (en) * 1992-10-07 1995-05-09 General Electric Company Method for making fatigue crack growth-resistant nickel-base article
US20110052409A1 (en) * 2009-08-31 2011-03-03 General Electric Company Process and alloy for turbine blades and blades formed therefrom
EP2469045A2 (de) 2010-12-23 2012-06-27 General Electric Company Turbinenflügelkomponenten, die Keramik-Materialien enthalten, und Verfahren dafür
EP2468434A1 (de) 2010-12-23 2012-06-27 General Electric Company Verfahren zur Herstellung von Bauteilen aus keramik-basierten und metallischen Werkstoffen
EP2469031A2 (de) 2010-12-27 2012-06-27 General Electric Company Turbinenschaufelkomponenten mit keramikbasierten Materialien und Verfahren dafür
EP2469026A2 (de) 2010-12-27 2012-06-27 General Electric Company Turbinenbauteile auf keramikbasierten Material und Beschichtungen hierfür
CN104203487A (zh) * 2012-03-28 2014-12-10 阿尔法拉瓦尔股份有限公司 新涂布概念
CN106086527A (zh) * 2016-07-26 2016-11-09 四川六合锻造股份有限公司 一种耐高温合金材料、其制备方法及其应用

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE561928A (de) *
US2570194A (en) * 1946-04-09 1951-10-09 Int Nickel Co Production of high-temperature alloys and articles
US2688536A (en) * 1951-01-27 1954-09-07 Gen Motors Corp High-temperature creep resistant alloy
US2712498A (en) * 1948-06-01 1955-07-05 Rolls Royce Nickel chromium alloys having high creep strength at high temperatures
US2809110A (en) * 1954-08-05 1957-10-08 Utica Drop Forge & Tool Corp Alloy for high temperature applications
CA548778A (en) * 1957-11-12 The International Nickel Company Of Canada Nickel-base heat-resistant alloy
US2860968A (en) * 1956-03-14 1958-11-18 Gen Motors Corp Wrought high temperature alloy
GB814029A (en) * 1956-10-29 1959-05-27 Mond Nickel Co Ltd Improvements in nickel-chromium-cobalt alloys
US2920956A (en) * 1956-10-08 1960-01-12 Universal Cyclops Steel Corp Method of preparing high temperature alloys
US2977222A (en) * 1955-08-22 1961-03-28 Int Nickel Co Heat-resisting nickel base alloys

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE561928A (de) *
CA548778A (en) * 1957-11-12 The International Nickel Company Of Canada Nickel-base heat-resistant alloy
US2570194A (en) * 1946-04-09 1951-10-09 Int Nickel Co Production of high-temperature alloys and articles
US2712498A (en) * 1948-06-01 1955-07-05 Rolls Royce Nickel chromium alloys having high creep strength at high temperatures
US2688536A (en) * 1951-01-27 1954-09-07 Gen Motors Corp High-temperature creep resistant alloy
US2809110A (en) * 1954-08-05 1957-10-08 Utica Drop Forge & Tool Corp Alloy for high temperature applications
US2977222A (en) * 1955-08-22 1961-03-28 Int Nickel Co Heat-resisting nickel base alloys
US2860968A (en) * 1956-03-14 1958-11-18 Gen Motors Corp Wrought high temperature alloy
US2920956A (en) * 1956-10-08 1960-01-12 Universal Cyclops Steel Corp Method of preparing high temperature alloys
GB814029A (en) * 1956-10-29 1959-05-27 Mond Nickel Co Ltd Improvements in nickel-chromium-cobalt alloys

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4957567A (en) * 1988-12-13 1990-09-18 General Electric Company Fatigue crack growth resistant nickel-base article and alloy and method for making
US5080734A (en) * 1989-10-04 1992-01-14 General Electric Company High strength fatigue crack-resistant alloy article
US5413752A (en) * 1992-10-07 1995-05-09 General Electric Company Method for making fatigue crack growth-resistant nickel-base article
US8597440B2 (en) 2009-08-31 2013-12-03 General Electric Company Process and alloy for turbine blades and blades formed therefrom
US20110052409A1 (en) * 2009-08-31 2011-03-03 General Electric Company Process and alloy for turbine blades and blades formed therefrom
EP2469045A2 (de) 2010-12-23 2012-06-27 General Electric Company Turbinenflügelkomponenten, die Keramik-Materialien enthalten, und Verfahren dafür
EP2468434A1 (de) 2010-12-23 2012-06-27 General Electric Company Verfahren zur Herstellung von Bauteilen aus keramik-basierten und metallischen Werkstoffen
US9228445B2 (en) 2010-12-23 2016-01-05 General Electric Company Turbine airfoil components containing ceramic-based materials and processes therefor
EP2469031A2 (de) 2010-12-27 2012-06-27 General Electric Company Turbinenschaufelkomponenten mit keramikbasierten Materialien und Verfahren dafür
EP2469026A2 (de) 2010-12-27 2012-06-27 General Electric Company Turbinenbauteile auf keramikbasierten Material und Beschichtungen hierfür
CN104203487A (zh) * 2012-03-28 2014-12-10 阿尔法拉瓦尔股份有限公司 新涂布概念
US20150044507A1 (en) * 2012-03-28 2015-02-12 Alfa Laval Corporate Ab Novel coating concept
US10335881B2 (en) * 2012-03-28 2019-07-02 Alfa Laval Corporate Ab Coating concept
CN106086527A (zh) * 2016-07-26 2016-11-09 四川六合锻造股份有限公司 一种耐高温合金材料、其制备方法及其应用

Also Published As

Publication number Publication date
GB893617A (en) 1962-04-11
CH398979A (de) 1966-03-15
BE589397A (fr) 1960-08-01

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