US3415641A - Wrought nickel base alloy - Google Patents

Wrought nickel base alloy Download PDF

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Publication number
US3415641A
US3415641A US574618A US57461866A US3415641A US 3415641 A US3415641 A US 3415641A US 574618 A US574618 A US 574618A US 57461866 A US57461866 A US 57461866A US 3415641 A US3415641 A US 3415641A
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alloy
sigma phase
nickel base
examples
aluminum
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US574618A
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English (en)
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Earl W Ross
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General Electric Co
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General Electric Co
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Priority to US574618A priority Critical patent/US3415641A/en
Priority to GB03351/67A priority patent/GB1177391A/en
Priority to BE698850D priority patent/BE698850A/xx
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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 base alloys suitable for use at elevated temperatures. More particularly, it relates to a wrought nickel base alloy having stability for long times at temperatures up to about l900 F. and having improved stress rupture and creep properties.
  • Sigma phase has been identified in some nickel base superalloys as a direct function of the quantities of certain strengthening elements.
  • strengthening elements such as the precipitation hardeners aluminum and titanium and the solution strengtheners tungsten, molybdenum and chromium have been added in increasing amounts, the frequency and amount of sigma phase formation has increased. This has been true particularly during long time exposure at elevated temperatures.
  • sigma phase Because the formation of sigma phase is a function of the alloy content, sigma phase will recur when the alloy is subjected to certain temperatures for periods of time even though sigma phase may be removed temporarily by heat treatment. Thus it has ⁇ been recognized that presently the formation of sigma phase can only be inhibited by a careful adjustment of the composition of the alloy. Unfortunately, studies prior to the discovery of the alloy of the present invention have shown that reduction of the hardening elements in nickel base superalloys result in a similar reduction in certain strength properties.
  • Another object is to provide a nickel ⁇ base alloy having improved long time stability, increased stress rupture life ann improved creep properties.
  • Still another object is to provide for a gas turbine en gine a wrought turbine blade capable of being used at elevated temperatures for long periods of time while at the same time maintaining improved strength and corrosion resistance characteristics.
  • FIG. 1 is a graphical presentation of the average stress rupture properties of Examples l-3 within the scope of the present invention.
  • FIGS. 2, 3 and 4 are graphical presentations of the rupture creep and yield strength properties of specimens of the alloy of the present invention taken from forged tur- Patented Dec. 10, 1968 bine blades compared with the -best commercially available wrought turbine blade alloy.
  • Fulfillment of the above objects can be achieved for a wrought nickel base superalloy by maintaining the car-bon level in the range of 0.2-0.3 weight percent and reducing the chromium content to the range of 9-12 weight percent, while at the same time carefully adjusting the strengthening elements Al, Ti, Mo and W in a nickel base including cobalt, boron and optionally zirconium. It was uexpectedly discovered that by reducing the chromium content for such alloys to the range of 9-12 weight percent, certain larger amounts of the strengthening elements aluminum and titanium could be added without causing sigma phase formation. This change did not reduce the alloys oxidation resistance up to about 1900 F. while inhibiting the formation of the detrimental sigma phase.
  • the composition of the alloy of the present invention consists essentially of, by Weight, 0.2-0.3% C; 0.005-0.002% B; llt-16% Co; 9-12% Cr; 3-4% Mo; 4.5-6% Al; 3-4% Ti; 5-6% W; up to about 0.05% Zr with the balance essentially nickel and incidental impurities, the sum of the A1 and Ti being in the range of 8-9%.
  • the solution strengthening elements molybdenum and tungsten are other elements in addition to the aluminum, titanium and chromium which along with carbon affect the long time stability of the alloy. As will be shown in detail later in connection with the examples, tungsten and molybdenum are included in particular ranges and are not interchangeable one with the other as is indicated to be possible in some prior work.
  • Examples 4 through 6 of Table I are outside the scope of the invention because in Example 4 the sum of the Al and Ti is too low with respect to the 8-9% range or because in Examples and 6 the alloy includes the element columbium. As will be shown in the following Table II, these differences though numerically small are significantly great as they relate to long time stress rupture properties and as they rel-ate to the formation of the detrimental sigma phase which affects the stability of the alloy.
  • the properties of the various alloy forms including the same elements as those within the scope of the present invention as well as Examples 5 and 6 including Columbium are shown in the following Table II.
  • Example 4 the primary difference is that the sum of the aluminum and titanium content is below the range of this invention.
  • the great difference in strength the detrimental effect of higher content, particularly of Ti, is shown in detail later with respect to Table III compositions.
  • Table III compositions the effect of the sum of the aluminum and titanium on sigma phase formation is critical.
  • Table ll as it relates to testing at 1500 F. and 45,000 p.s.i. of the examples of Table I shows the same significant strength property differences based on metal structure differences though the chemistry may appear numerically to be relatively close.
  • Columbium is sometimes included in other nickel base alloys as a precipitation hardener.
  • the effect of Columbium on long time stress rupture strength and sigma phase formation is easily seen from the data of Table II by the medium-heavy sigma phase formation. Therefore, the elements aluminum and titanium have a different effect on the lalloy of the present invention than does the element Columbium in the presence of higher carbon within the range of the present invention.
  • alloying additions greater than the composition of the present invention tend to cause sigma phase formation and are to be avoided.
  • Examples l, 2 and 3 fall within the scope of the present invention whereas Examples 4 through 6 are outside the scope.
  • Examples 1 through 3 have stress rupture lives of 973-1312 hours with good ductility and little, if any, sigma phase formation when tested at 1600 F. under a stress of 35,000 p.s.i.
  • Examples 4 through 6 either were too weak to be considered as an improved structural material or had significant amounts of sigma phase formation or both.
  • Example 7 was selected as a representative one of that group for testing because its variation from the alloy of the present invention existed in a lower carbon content, higher aluminum content and higher sum of the aluminum and titanium precipitation hardeners.
  • the long time stress rupture properties of Examples 7 through 11 are shown in the following Table IV.
  • the alloy of Example 7 shows that the combination of Ihigh aluminum and the high sum of -aluminum and titanium, coupled with lower carbon in the range of about 0.16%, results in very low stress rupture life and a heavy sigma phase formation. This is a significant structural difference between the alloy of Example 7 and that of the present invention. "Although the alloy of Example 8 is signicantly lbetter than the other alloy forms in Table III, nevertheless comparing it with Examples l, 2 and 3 in Table II it can be seen that there is a signicant difference between the stress rupture life of the alloy of Example 8 and those Within the scope of the present invention.
  • the alloy of Example 9, with the proper carbon range of this invention shows a significantly reduced long time stress rupture life at the higher aluminum and titanium levels and a heavy formation of the detrimental sigma phase.
  • the range of cobalt has been maintained at a level of about 14-16 weight percent because of widely documented and published work that the range of about /14-16 weight percent cobalt in an alloy of a type to which the present invention relates results in improved workability.
  • boron can be included in the range of 0.005-0.02% and in some instances zirconium up to about 0.05 weight percent can be included.
  • An improved wrought nickel base alloy having a stress rupture life of greater than 900 hours at 1600 F. and 35,000 p.s.i. stress and virtually no sigma phase formation during such time, the alloy consisting essentially of, by weight:
  • the alloy of the present invention by avoiding the forming of sigma phase through a specially controlled composition, provides the turbine designer with a signifiwith the balance Ni and incidental impurities. 2.
  • the alloy of claim 1 in which:
  • Al is 5-5.5% and Ti is 3-3.5%.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US574618A 1966-08-24 1966-08-24 Wrought nickel base alloy Expired - Lifetime US3415641A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US574618A US3415641A (en) 1966-08-24 1966-08-24 Wrought nickel base alloy
GB03351/67A GB1177391A (en) 1966-08-24 1967-03-22 Improvements in wrought nickel base alloy.
BE698850D BE698850A (ref) 1966-08-24 1967-05-23

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US574618A US3415641A (en) 1966-08-24 1966-08-24 Wrought nickel base alloy

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3536542A (en) * 1968-05-31 1970-10-27 Gen Electric Alloy heat treatment
US5551999A (en) * 1984-04-23 1996-09-03 United Technologies Corporation Cyclic recovery heat treatment
US5725692A (en) * 1995-10-02 1998-03-10 United Technologies Corporation Nickel base superalloy articles with improved resistance to crack propagation
US5820700A (en) * 1993-06-10 1998-10-13 United Technologies Corporation Nickel base superalloy columnar grain and equiaxed materials with improved performance in hydrogen and air

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111235434B (zh) 2020-03-02 2021-07-30 北京钢研高纳科技股份有限公司 一种高温使用的镍基变形高温合金轮盘锻件的制备方法

Citations (4)

* 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
US2951757A (en) * 1958-03-07 1960-09-06 Westinghouse Electric Corp High temperature nickel base alloy
US3293030A (en) * 1962-05-12 1966-12-20 Birmingham Small Arms Co Ltd Nickel-base alloys
US3322534A (en) * 1964-08-19 1967-05-30 Int Nickel Co High temperature nickel-chromium base alloys

Patent Citations (4)

* 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
US2951757A (en) * 1958-03-07 1960-09-06 Westinghouse Electric Corp High temperature nickel base alloy
US3293030A (en) * 1962-05-12 1966-12-20 Birmingham Small Arms Co Ltd Nickel-base alloys
US3322534A (en) * 1964-08-19 1967-05-30 Int Nickel Co High temperature nickel-chromium base alloys

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3536542A (en) * 1968-05-31 1970-10-27 Gen Electric Alloy heat treatment
US5551999A (en) * 1984-04-23 1996-09-03 United Technologies Corporation Cyclic recovery heat treatment
US5820700A (en) * 1993-06-10 1998-10-13 United Technologies Corporation Nickel base superalloy columnar grain and equiaxed materials with improved performance in hydrogen and air
US5725692A (en) * 1995-10-02 1998-03-10 United Technologies Corporation Nickel base superalloy articles with improved resistance to crack propagation
US5788785A (en) * 1995-10-02 1998-08-04 United Technology Corporation Method for making a nickel base alloy having improved resistance to hydrogen embittlement

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BE698850A (ref) 1967-11-03
GB1177391A (en) 1970-01-14

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