US3467516A - Wrought nickel base alloy - Google Patents

Wrought nickel base alloy Download PDF

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Publication number
US3467516A
US3467516A US546647A US3467516DA US3467516A US 3467516 A US3467516 A US 3467516A US 546647 A US546647 A US 546647A US 3467516D A US3467516D A US 3467516DA US 3467516 A US3467516 A US 3467516A
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alloy
alloys
present
nickel base
properties
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US546647A
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James F Barker
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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

  • This invention relates to nickel lbase alloys and, more particularly, to an improved fabricable nickel base sheet alloy having improved weldability and resistance to subsequent weld cracking along with a good balance of stable tensile and stress rupture properties between room tem- .perature and about 1800 F.
  • a principal object of this invention is to provide a nickel base alloy which can be reduced to sheet form and which has an improved balance of tensile and stress rupture properties between room temperature and about 1800 F. along with the capability of being welded, heat treated after welding and repair ⁇ welded Without detrimental cracking.
  • nickel base super alloys In general two major Vstrengthening mechanisms are considered with nickel base super alloys. One of these involves the solid solution strengthening of the alloy through the use of such elements as tungsten and molybdenum. The other is the precipitation strengthening mechanism involving the use of such elements as titanium, aluminum, columbium, etc. in the presence of carbon in the nickel ibase to precipitate various carbides or various complex phrases.
  • the present invention recognizes a critical relationship and effect between the individual solution strengthening elements and the individual precipitation hardening elements as separate groups as well as complex balance and interrelationship between these two groups of elements.
  • Typical of the alloy forms within the scope of the present invention are those, the compositions of which are shown in the following Table I.
  • the various alloy compositions in Table I as well as those other alloys shown in the various tables which follow were evaluated first for solution heat treatment to find the gamma prime phase solution temperature.
  • the gamma prime solution temperature was found to lie within the range of 2000-2150 F. and primarily 2050-2l50 F. Therefore, such range was selected as the solution heat treatment temperature for the hot rolled sheet material specimens prior to property evaluation.
  • a typical aging treatment for nickel base super alloys was selected to be at about 1400 F. for a normal period of time such as 16 hours.
  • Table II lists the tensile and stress rupture properties of the alloy forms of Table I both at room and elevated 3 templ'atlll's aS ShOWIl.
  • the annealing heat treatment was 2025* F. for 10 minutes, furnace cool to 1950* F. in four hours then water quench prior to welding into the fixture.
  • the stress relief treatment was accomplished by inserting the patch test assembly into a furnace preheated 3 hours at 2100 F. It was held there for 10 minutes and then furnace cooled at the rate of 30 F. per minute to 1200" F. Aging was performed at 1400 F. for 16 hours after which it was air cooled.
  • the alloys of the present invention pass successfully this critical weldability evaluation.
  • alloy of the present invention are a number of other alloys some of which have either tensile or stress rupture strengths or both slightly better than some forms of the present invention.
  • Such other alloys outside the scope of the present invention do not provide the unusual combination of good strength properties combined with weldability so important to the use of an alloy in sheet form.
  • the weldability evaluation used in connection with the alloy of the present invention involved welding to a strong retaining back member -a 31/2 diameter first disc of 0.05-0.06" sheet having a 1%.” diameter central opening.
  • the back member was a 1/2 thick square plate each side of which was 6%" long and including a 3 diameter central opening.
  • the welding stresses produced in this configuration have been found to be equal to the yield strength of the test material and simulate the conditions found in a welded fabrication.
  • the patch test assembly is then given the prescribed heat treatment for the alloy and later a repair test weld is placed radially inwardly from but adjacent the 1'1/2 diameter weld around the central plug.
  • the other element which was maintained in the alloys of Table IV within the range of the present invention is boron.
  • the inclusion of boron at above about 0.02% tends to cause incipient melting of the alloy and hot shortness or poor ductility when being worked at elevated temperatures.
  • the element cobalt has been included in the alloy of the present invention in the range of about 13-16% for its benefit on hot workability. Some of the alloys of Table IV, all of which are outside the scope of the present invention, included cobalt within the range of the present invention for comparison purposes. In addition, cobalt levels between 10 and 25% are included to show that increased amounts of cobalt outside the present invention range at higher levels assist in improved stress rupture life but at the expense of much lower tensile ductility.
  • solutioning temperatures greater than about 2150 F. used in the evaluation of this invention, have been shown to approach the incipient melting point of the lower melting alloy constituents.
  • the carbon range of the present invention has been selected specifically to provide more than required for deoxidization but less than that amount which will inhibit grain growth. Such range results in the formation of agglomerated carbides while at the same time allowing the use of practical solutioning temperatures well below the incipient melting point of any of the lower melting alloy constituents in order to maintain good properties.
  • the alloys ofv Examples 24 and 26 could be reduced to sheet form because of the significantly greater amount of cobalt included in the alloy composition. However, the tensile properties of the resulting alloy is low, particularly the tensile ductility.
  • Example 8 which has slightly less of a total of aluminum and titanium could be reduced to sheet form but was very brittle as shown-by the tensile ductility of only 1% elongation and the substantially same ultimate tensile strength and 0.2% yield strength.
  • Example 7 At the other end of spectrum of alloys the compositions of which are shown in Table IV is the alloy of Example 7 which is within the scope of the present invention except for the sum of the aluminum and titanium content and the carbon content. Referring to Table V, it is seen that Example 7 has good tensile and stress rupture properties. Nevertheless, as will be shown in the following Table VI, alloy 7 cracked in the stress relief step after welding and after being solution heat treated at 2l00 F. for 1/2 hour followed by air cooling. The mild nature of this cracking indicates the sum of the Al and Ti contents were slightly in excess of that desirable for the best weldability.
  • alloy 18 includes a lower total amount of aluminum and titanium. As a result, the tensile properties are somewhat reduced and the stress rupture strength is significantly reduced. Other variations in aluminum and titanium content are shown in Table IV and the corresponding strength properties are shown in Table V.
  • compositions shown in Table 1V were varied, in addition, to show the effect of the solution strengthening elements molybdenum and tungsten on the alloy of the present invention and to show that such elements are not interchangeable even on an atomic basis.
  • the alloy of the present invention includes molybdenum and tungtens in the range of 5.5-7 weight percent molybdenum and 1.4-3.5 weight percent tungsten.
  • a com parison should be made between Example 7, including 5.5% Mo and 3.2% WWith Example 1l, including 3.4% Mo and 5.4% W with the same total of precipitation hardening elements aluminum and titanium.
  • Table VI shows that Example ll could not even be welded because of severe transverse cracking on welding whereas Example 7 was at least weldable even though it cracked on stress relief.
  • alloys of the nickel base super alloy type can tolerate iron in relatively large amounts, iron is specifically excluded, except perhaps as a slight impurity, in the alloy of the present invention because of its tendency to reduce stress rupture properties.
  • Example 1 there is shown a comparison between the alloy form of Example 1 within the scope of the present invention as shown in Table I, that of another reported alloy A having a composition, by weight, of 0.05% C, 2.0% Al, 3.0% Ti, 6.0% Mo, 19.0% Cr, 12.0% Co, 1.0% W with the balance substantially nickel and a well known Alloy B having a composition, by weight, of 0.05% C, 3.0% Al, 3.0% Ti, 4.0% Mo, 17.5% Cr, 16.5% Co with the balance essentially nickel and incidental impurities and including no tungsten.
  • the superiority of the present invention over a wide range is shown.
  • the graph form is the Larson-Miller parameter type reported in the Transactions of the American Society of Merchanical Engineers, 1592, vol. 74, at pages 765-771.
  • An improved, Wrought nickel base alloy characterized by improved weldability in sheet form along with good strength properties up to about 1800 F., the alloy consisting essentially of, by weight:
  • W is 2.5-3.5%.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Heat Treatment Of Steel (AREA)
  • Powder Metallurgy (AREA)
US546647A 1966-05-02 1966-05-02 Wrought nickel base alloy Expired - Lifetime US3467516A (en)

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BE (1) BE693506A (en))
CH (1) CH484280A (en))
ES (1) ES336314A1 (en))
FR (1) FR1509889A (en))
GB (1) GB1122269A (en))
NL (1) NL6701647A (en))
SE (1) SE306429B (en))

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2809110A (en) * 1954-08-05 1957-10-08 Utica Drop Forge & Tool Corp Alloy for high temperature applications
US2975051A (en) * 1959-09-29 1961-03-14 Gen Electric Nickel base alloy
US2977222A (en) * 1955-08-22 1961-03-28 Int Nickel Co Heat-resisting nickel base alloys
US3107167A (en) * 1961-04-07 1963-10-15 Special Metals Inc Hot workable nickel base alloy
US3110587A (en) * 1959-06-23 1963-11-12 Int Nickel Co Nickel-chromium base alloy
US3155501A (en) * 1961-06-30 1964-11-03 Gen Electric Nickel base alloy
US3385698A (en) * 1965-04-09 1968-05-28 Carpenter Steel Co Nickel base alloy

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US3110587A (en) * 1959-06-23 1963-11-12 Int Nickel Co Nickel-chromium base alloy
US2975051A (en) * 1959-09-29 1961-03-14 Gen Electric Nickel base alloy
US3107167A (en) * 1961-04-07 1963-10-15 Special Metals Inc Hot workable nickel base alloy
US3155501A (en) * 1961-06-30 1964-11-03 Gen Electric Nickel base alloy
US3385698A (en) * 1965-04-09 1968-05-28 Carpenter Steel Co Nickel base alloy

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BE693506A (en)) 1967-07-17
ES336314A1 (es) 1967-12-16
FR1509889A (fr) 1968-01-12
SE306429B (en)) 1968-11-25
NL6701647A (en)) 1967-11-03
CH484280A (de) 1970-01-15
GB1122269A (en) 1968-08-07

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