US3157495A - Alloy characterized by controlled thermoelasticity at elevated temperatures - Google Patents

Alloy characterized by controlled thermoelasticity at elevated temperatures Download PDF

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US3157495A
US3157495A US232084A US23208462A US3157495A US 3157495 A US3157495 A US 3157495A US 232084 A US232084 A US 232084A US 23208462 A US23208462 A US 23208462A US 3157495 A US3157495 A US 3157495A
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alloy
alloys
thermoelastic
temperature
tantalum
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Herbert L Eiselstein
James K Bell
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Huntington Alloys Corp
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International Nickel Co Inc
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Priority to CH1293963A priority patent/CH426274A/fr
Priority to SE11570/63A priority patent/SE302371B/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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/001—Ferrous alloys, e.g. steel alloys containing N
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/10—Ferrous alloys, e.g. steel alloys containing cobalt
    • C22C38/105—Ferrous alloys, e.g. steel alloys containing cobalt containing Co and Ni

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  • the present invention relates to novel iron-nickelcobalt-columbium alloys, and more particularlyto age hardenable iron-nickel-cobalt-columbium alloys which, in the hardened condition, exhibit a controlled thermoelastic coeflicient and a high level of strength over a Wide range of temperature.
  • thermoelasticity Youngs modulus of elasticity with variations in temperature
  • the proportionate change in the modulus per unit change in temperature has been known as the temperature coefficient of Youngs modulus of elasticity.
  • the most common type of thermoelasticity is a decrease in Youngs modulus with an increase in temperature, i.e., the temperature coeificient of Youngs modulus is negative.
  • the primary result of a decrease in modulus of elasticity is a reduction in n'gidity of the structure and an increase of deflection under load as the temperature increases.
  • resilient elements such as vibratory reeds, mechanisms and springs made of usual alloys and employed in operation over a range of temperatures undergo changes in essential characteristics, e.g., vibratory reeds suifer a change in resonant frequency, and springs no longer exert the same force when deflected a given amount.
  • the problems are further complicated when the variation of the modulus with temperature is not substantially uniform, thus increasing the difficulty and/ or limiting the accuracy of measures to compensate for variations in the modulus.
  • thermoelasticity One means of overcoming the disadvantages of thermoelasticity is to use special alloys which have thermoelastic characteristics specially adapted for particular situations, if such special alloys are available.
  • the structure of an alloy characterized by a temperature coefiicient of Youngs modulus equal to zero throughout that range of temperature.
  • the structure be made of an alloy having a temperature coefficient of Youngs modulus greater than zero, i.e., of positive value, throughout that range of operating temperatures.
  • thermoelastic coefiicient T.E.C.
  • therrnoelastic coefiicient being the algebraic sum of the temperature coeflicient of Youngs modulus of elasticity plus the temperature coefiicient of linear expansion.
  • an elongated ice element of uniform cross section have a constant resonant frequency throughout a range of temperatures when vibrating in the manner of a tuning fork
  • the element be made of an alloy having a thermoelastic coefiicient equal to zero throughout that range of temperatures.
  • the spring be made of an alloy having a thermoelastic coefiicient of zero throughout that range of temperatures.
  • thermoelastic coefiicient be a positive or negative value throughout the range of operating temperatures and that the thermoelastic coefiicient be uniform, i.e., that the variation of modulus with temperature be uniform.
  • Alloys which are produced under one or more 'spe cial controls which provide that the finished alloy be characterized by a thermoelastic coefiicient approximately equal to a preselected value are referred to as being characterized by a controlled thermoelastic coefficient.
  • These special controls include control of the composition, control of the heat treatment and control of the amount of cold working of the alloy.
  • alloys have characteristics permitting them to be readily fabricated by economical methods. Such alloys should be malleable in the hot state, and be suitable for cold forming, brazing and Welding. Also, the requisite mechanical properties must be attainable by relatively simple heat treatments, and unusually difiicult operations such as very high degrees of cold working should not be necessary. Furthermore, the alloys should not contain large amounts of readily oxidizable elements which can cause difficulties in casting or promote rapid oxidation during service at elevated temperatures.
  • alloys have been designed to retain a constant modulus of elasticity over a very limited range of temperatures, and other alloys have been developed which retain high levels of strength at elevated temperature.
  • operating temperatures range from room temperature or lower up to about 600 F. or higher
  • metallic structures made of known alloys are subject to either or both of the detrimental effects of substantial variations in modulus of elasticity, and/or low tensile strength.
  • Alloys have now been discovered containing especially correlated amounts of nickel, cobalt, iron and columbium which, in the age hardened condition, have an advantageous combination of properties including controlled thermoelastic coefficients and high levels of strength over a relatively wide range of temperatures.
  • These new alloys canbe readily fabricated by casting, hot working, cold working, brazing or welding, and, when age hardened, are metallurgically stable at temperatures up to at least 900 F.
  • Another object of the invention is to provide alloys which can be processed by heat treatment with the option of cold working to be characterized by high strength and by substantially uniform thermoelastic coefiicients controlled to be approximately equal to any required value from about minus 50x10 F. to about plus 125' 10 /F. throughout the temperature range of from about room temperature to at least about 600 F. by control of alloy composition and heat treatment either with or without cold working.
  • the invention also contemplates providing alloys characterized by ferromagnetism and by thermoelastic coefficients which are controlled to be about equal to any required value from about minus 50 10- F. to about plus 125 10- F., throughout the temperature range from about 80 F. up to at least about 600 F.
  • his a further object of the invention to provide an alloy which undergoes only a very moderate change in modulus of elasticity and retains a high level of strength when heated in the temperature range from room temperature or lower to up to at least about 600 F.
  • the invention further contemplates providing an age hardened alloy which retains a high level of strength and is metallurgically stable when repeatedly heated and cooled throughout the temperature range of about 80 F. to 900 F.
  • resilient elements made from an age hardened nickel-cobalt-ironcolumbium alloy having high strength at elevated temperatures together with an advantageously controlled thermoelastic coefiicient over a temperature range of from room temperature or lower to at least about 600 F., and which is readily fabricated by casting, working, machining, brazing and/or welding.
  • FIGURE 1 is a graph comparatively depicting the thermoelast'ic characteristics over a range of temperatures of an alloy of this invention, and those of two commercially available alloys outside of the invention.
  • FIGURE 2 is a graphical illustration of the eiiect of positive and negative thermoelast-ic coeificients uponthe resonant frequency of a vibrating element.
  • the present invention contemplates alphorus.
  • columbium with or without small amounts of tantalum in percentages such that the total of the percent columbium plus one-half the percent of any tantalum present is from about 2.4% to about 6%, about 0.5% to about 1.5% titanium, with the balance substantially iron in an amount not less than about 31% of the alloy.
  • the balance of the alloys can also includes up to about 1% aluminum, up to about 1% silicon, up to about 1% manganese, up to about 0.2% carbon, e.g., not more than about 0.1% carbon, up to about 0.1% calcium, and small amounts of incidental elements and impurities normally associated with the alloying, ingredients such as up to about 1% copper, up to about 0.05% sulfur, and up to about 0.05% phos- Elements such as chromium, molybdenum and tungsten are detrimental to the thermoelastic characteristics and while minor amounts of these elements may be present as impurities, the amount of each should be less than 1%.
  • the maximum nickel content is about 44% and the maximum cobalt content ,is about 47%. 7
  • the balance index of the alloy the sum of 1.235 times the percent nickel, plus the percent cobalt in an alloy of the invention.
  • the balance index is in the range of 55.8 to 66.8.
  • the alloys of the invention can be age hardened by heat treating at temperatures of about 1100 F. to about 1300" F. for about 4 to about 24 hours.
  • the alloys are characterized by high strength, by thermoelastic coeiiicients which are uniform and controlled up to temperatures of at least 600 F., and by metallurgical stability up to at least 1000" F.
  • the alloys are annealed prior to age hardening, a satisfactory annealing treatment comprising heating an,
  • An advantageous annealing treatment comprises heating the alloy at a temperature of about 1800 F. to about 1850" F. for about one hour and thereafter water quenching the alloy.
  • the alloys of the invention can be cold worked after annealing and before age hardening and alloys so processed will be referred to hereinafter as cold worked and age hardened alloys, whereas annealed and age hardened alloys which have not been cold worked will be referred to controllable is herein termed the inflection temperature. This term is defined in more detail in the. subsequent discussion of FIGURE 2.
  • the inflection temperatures of the hereinbefore defined alloys are not less than about 600 F.
  • thermoelastic coefiicients of alloys within the invention are controlled to a major extent by controlling the compositions of the alloys to have balance indexes corresponding to the required thermoelastic coefficients.
  • a low thermoelastic coeilicient i.e., a thermoeleastic coefiicient of absolute value not greater than about 50 10- F.
  • thermoelastic coefiicient near zero i.e., a thermoelastic coefiicient of absolute value not greater than about 20 l0* F.
  • the inflection temperature of such an alloy of the invention will be at least about 725 F.
  • alloys can also be produced in accordance with the invention so as to be characterized in the annealed and age hardened condition by inflection temperatures of not less than about 600 F. and by positive thermoeleastic coefficients in the range of from about 50 10- F. to about 125x 10 F. by controlling the composition to have a balance index in the range of 55.8 to 60.4.
  • Such alloys are advantageous where it is necessary that a structure have increased stillness when the temperature of the structure is increased throughout a range of temperatures, or when it is necessary to compensate for the thermoelasticity of other structures.
  • More advantageous alloys contain at least about 16% ickel, at least about 24% cobalt, with the nickel and cobalt contents bein controlled to provide a balance index of 62.2 to 64.8, columbium with or without small amounts of tantalum in percentages such that the total percent columbium plus one-half the percent tantalum is from about 2.4% to about 6% of the alloy, about 0.5% to about 1.5% titanium, and the balance substantially iron.
  • the balance of the alloys can also include up to about 1% aluminum, up to about 1% silicon, up to about 1% manganese, up to about 0.1% carbon, up to about 0.1% calcium and the small amounts of incidental elements and impurities referred to hereinbefore.
  • thermoelastic coefficients near zero and infiection temperatures not lower than about 900 F. e.g., 900 F. to 1050 F.
  • thermoelastic coefficients near zero e.g., 900 F. to 1050 F.
  • All alloys of the invention when age hardened are characterized by high strength at room temperature and at elevated temperatures, i.e., these alloys have an ultimate tensile strength at room temperature of at least 125,000 pounds per square inch and a stress-rupture life of at least 10 hours when subjected to a tensile load of 90,000 pounds per square inch at900 F.
  • the aforestated alloys of the invention can be produced with higher tensile strength and higher minimum stress-rupture life by advantageously controlling the columbium content or the total of the percent columbium plus one-half the percent tantalum to be from about 3% to about 6%. With the composition thus controlled, the alloys when age hardened within the range of about 1100 F. to about 1300 P.
  • the alloys when age hardened in the aforestated temperature range will have a minimum stress-rupture life of about 200 hours at 900 F. and 90,000 p.s.i., and a minimum tensile strength at room temperature of about 175,000 p.s.i.
  • thermoelastic characteristics of an alloy of the invention are shown and compared with those of two commercially available alloys (Alloys A and B) in FIGURE 1.
  • Compositions of these alloys and other examples of the invention are set forth in Table I.
  • the elastic modulus of Alloy 11 of the invention undergoes far less change in the temperature interval from about F. to about 800 F. than do the elastic moduli of Alloys A and B.
  • the change over this temperature range in the Youngs modulus of Alloy A is about 10.2%, Alloy B about 5.8%, and for Alloy 11 less than 0.1%. Where temperatures exceed about 275 F.
  • the plot of the modulus of Alloy B is particularly non-linear in that the plot has two inflection points, illustrating the fact that the modulus of Alloy B does not vary uniformly with temperature, but instead varies in an inrregular manner which would render compensation difiicult, or even impossible, in devices intended'to operate at temperatures exceeding about 275 F.
  • the plot for Alloy 11 is almost a straight horizontal line, indicating that the variation of the Youngs modulus of the alloy of this invention is very small, and that the small variation that does occur is uniform and predictable.
  • Balance of alloys 1 through 19 includes about 0.5% silicon, 0.4% manganese, 0.03% copper and 0.003% to 0.013% sultur 2 Tantalum is present in these alloys to the extent of about 5% to 15% of the indicated total percent of columbium plus tantalum.
  • FIGURE 2 the thermoelastic behavior of alloys throughout a range of temperatures is shown qualitatively to illustrate the determination of inflection temperatures and calculation of the thermoelastic coefiicients of alloys as employed herein.
  • This figure shows two plots of resonant-frequency in transverse vibration against ten perature. The variation of resonant frequency with temperature is indicated in FIGURE 2 in an exaggerated degree for clarity of illustration and is not exemplary of the magnitude of the variations characteristic of alloys of the invention, but the smoothly curved shapes of the plots do illustrate the uniformity of the thermoelastic coefiicients characteristic of alloys of the invention.
  • thermoelastic coefficient refers to the average thermoeiastic coeilicient measured between about 80 F.
  • thermoelastic coefficient (T.E.C.) is calculated according to the formula where f and f are the resonant frequencies at room temperature and the inflection temperature, respectively, and RT. and LT. are room temperature and inflection temperature in degrees Fahrenheit. In accordance with this formula, the thermoelastic coefficient is in units per degree Fahrenheit. Room temperature, i.e., about 80 F., is used herein as the lower end of the temperature range unless otherwise specified.
  • thermo-elastic coeflicient of absolute value not greater than a given number up to at least a given temperature
  • thermoelastic coetficient has an absolute (i.e., regard.
  • the inflection temperature is the maximum satisfactory operating temperature for a device dependent for satisfactory' operation upon an element having a uniform and controlled thermoelastic coeficient.
  • the alloys of the invention are ferromagnetic at temperatures up to the inflection temperatures of the alloys and are useful in the production of devices which are responsive to, or actuated by, magnetic flux at temperatures up to the inflection temperatures of the alloys.
  • Thermoelastic coefiicients and inflection temperatures of examples of alloys of the invention and of Alloys A and B were determined by first determining the resonant frequencies at various temperatures ranging from room temperature to about 900 F., and then plotting the results as in the graph of FIG. 2.
  • the resonant frequencies were determined by transversely vibrating a specimen of the alloy at a controlled temperature and measuring the resonant frequency in a test procedure similar to that of Roberts and Northcliffe, as described in Measurement of Youngs Modulus at High Temperatures by M. H. Roberts and J. Northcliffe, published in the Journal of the Iron and Steel lnsttiute, p. 345, November 1947.
  • thermoelastic coeiiicients and inflection temperatures of Alloys A and B and of Alloys 1 through 19 of the present invention, all in the heat-treated condition are set forth in Table II. It is to be noted that although the data in Table II relates to determinations using 80 F. as the low limit of the testing range, the thermoelastic coeificients of alloys of the invention do not change greatly at substantially lower temperatures, e.g., temperatures down to about minus 100 F. or minus 320 F. For example, the thermoelastic coefiicient of Alloy 13 was also determined over the temperatures range of minus 100 F. to 825 F., and found to be about minus 22 l0- F.
  • Alloys suchas Alloys 11 and 12 of Table II are specially advantageous for use where it is desired that an annealed and age hardened alloy be characterized by high strength and by a thernioelastic coefficient very close to zero up to at least about 750 F., and an alloy such as Alloy 9 of Table II is specially advantageous where it is desired 7 that an annealed and age hardened alloy be characterized byhigh strength and by a thermoelastic coefiicient of absolute value not greater than about l0'- F. up
  • thermoelastic coefiicients of Alloys A and B were calculated for the temperature range F. to 800 F. in order to compare the thermoelastic coefficients of these alloys with the thermoelastic coefficient of Alloy 11.
  • the alloys of the present invention are produced by V melting the ingredients in an induction furnace or any of the other production furnaces employed for similar alloys to result in alloys of the aforestated compositions and then castinginto ingots and hot-forging said ingots, or by casting said alloys as finally shaped castings.
  • Elements such as manganese, slicon, calcium and aluminum can be added to the alloy while molten for purposes of deoxidation, purification, and malleability.
  • Titanium in the alloy also serves these purposes.- Titanium, advantageously about 0.5% to about 1% titanium, and aluminum, advantageously about 0.25% to about 0.75% aluminum, also serve to increase the age hardenability and the strength of the alloy.
  • the titanium content should not exceed 1.5% in order to avoid adverse effect upon the ductility and the thermoelastic characteristics of the alloysof the invention.
  • Annealing of forgings or castings at about 1800 F. to 1850 F. is advantageous for purposes of homogenizing the structure and/ or softening the alloy for cold working or machining. Brazing and welding operations are also better performed after annealing. After fabricating operations are complete, age hardening is accomplished as'previously described.
  • thermoelastic coefiicient of the finished age hardened alloy is principally governed by the composition and the processing steps of age hardening with or without cold working, and these factors are controlled to adjust said coefficient. It should be understood that it is sometimes advantageous to produce an alloy with a coefiicient which is not exactly zero, but which has a controlled positwo or negative value.
  • the alloy composition of this invention is specially designed to provide that the thermoelastic coefficient can be adjusted by a predictable method, this method being to control the amounts of nickel and cobalt so as to adjust the balance index of the alloy.
  • thermoelastic coefiicient of an annealed and age hardened alloy of the invention is adjusted proportionately from a value of about plus 125 10 F. to a value of about minus 50 10- F. approximately, i.e., within about plus or minus x10 R, according to the formula where B1. is the balance index.
  • thermoelastic coefficient of the age hardened alloy can be more negative (or less positive) and to increase the inflection tempera ture by a small amount, the magnitude of these efiects being dependent upon the amount of cold work performed.
  • the age hardening temperature can be adjusted toward the upper limit of the aforementioned range.
  • a compensating heat treatment can be performed on cold worked alloys of the invention between the steps of cold working and age hardening. Such a compensating heat treatment is accompli hed by heating the cold Worked alloy at a temperature of about 1500 F. to 1600" F. for about one hour and then rapidly cooling, e.g., water quenching, the alloy.
  • the composition of the alloy in producing a cold worked and age hardened alloy having a thermoelastic coefficient controlled to be equal to a required value, the composition of the alloy is con trolled within the ranges and limits of the invention to result in a balance index which is lower than the balance index of an alloy that would be characterized by the same required thermoelastic coefi'icient after annealing and age. hardening without cold working.
  • an alloy of the invention is to be cold Worked to about reduction in area and age hardened at about 12tl0 R, such control is exercised to provide that the finished alloy be characterized by a thermoelastic coefhcient near a required value, i.e., Within about plus or minus 20 10 F.
  • the composition of the alloy by controlling the composition of the alloy to provide that the cobalt content be about 12.5 to about 28% and that the balance index be in the range of about 57 to 65.5 and be of such a value in relation to the required thermoelastic coeflicient as to satisfy the formula Required T.E.C.:1l.6(6l.2-B.l.) X 10 F.
  • thermoelastic coefiicient of absolute value not greater than about 10 F. up to at least about 725 F.
  • the composition of an alloy within the composition of the invention by controlling the cobalt content to be about 12.5% to 28% of the alloy and controlling the amounts of nickel and cobalt to provide that the balance index be in the range of 60.4 to 65.5.
  • the nickel content of such alloys is at least about 26.2%.
  • thernioelastic coeificients and inflection tem- 1Q peratures of some of the alloys shown in Table I when in the cold worked and age hardened condition are set forth in Table 111.
  • Treatment X10 /F Heat treatments (after cold rolling) A5 hours at 1200 F. B-l hour at 1500 F.; water quenched, 5 hours at 1200 F. C1 hour at 1600 I 1; Water quenched; 5 hours at 1200 F.
  • Alloys of Table ill were annealed after hot forging by heat treating at 1800 F. for one hour and water quenching.
  • the alloys were then 44% cold rolled, i.e., cold rolled to a reduction in cross sectional area of about 44%, and heat treated as set forth in the table.
  • heat treated according to heat treatment B are specially advantageous for use where it is required that a cold rolled and age hardened alloy be characterized by high strength and by a thermoelastic coefficient very close to zero up to at least about 900 F.
  • alloys of Table IE can be processed to be characterized by thermoelastic coefiicients intermediate the thermoelastic coefficients set forth in Tables 11 and ill by cold working an amount less than'44% cold rolling.
  • the alloys of the invention are characterized by very useful levels of strength and ductility when age hardened without being cold worked, and the tensile strength is even greater when the alloys have been cold Worked.
  • Tensile properties of examples of age hardened alloys of compositions set forth in Table I are set forth in Table IV, and tensile properties of examples of cold Worked and age hardened alloys of some of the same compositrons are set forth in Table V. Alloys set forth in Tables 1V and V were hot forged, then annealed by heat treating for one hour at 1800 F. to 1850 F. and Water quenching, and thereafter hardened by aging at 1200 F. Alloys set forth in Table V were 44% cold rolled after annealing and before aging.
  • ductility is decreased by cold working, a substantial amount of ductility, i.e., that equivalent to at least about elongation after fracture in a room temperature tensile test, is still present after age hardening when the columbium content is about 2.7% and the alloys have been 44% cold rolled. It is to be noted, however, that ductility in the usual sense, i.e., plastic ductility, is not a requisite for most uses of the alloys of the invention since these alloys will usually be used in structures which are not plastically deformed during use.
  • an elastically operable element which plays a critical role in measuring be made of an alloy in a condition characterized not only by a thermoelastic coeflicient not greater than about 50 10- F., but also by high yield strength and very low plastic ductility.
  • Such an element will have high resistance to plastic deformation, but if it is overstressed, i.e., stressed beyond the elastic limit of the alloy, it will fracture rather than undergo a substantial amount of plastic deformation.
  • This condition is advantageous where it is desirable that, in event of overstressing, a measuring instrument become inoperative rather than continue to operate and produce erroneous measurements.
  • Alloys 3 and 5, of Table V are examples of such alloys in a condition advantageously characterized by high yield strength and low plastic ductility, as well as thermoelastic coeflicients of absolute value not greater than about 50x l0 F. up to temperatures of at least 750 F.
  • a particularly important advantageous characteristic of alloys of the present invention is that in the age hardened condition these alloys possess a highly useful level of strength at elevated temperatures.
  • the stress-rupture properties of some of the alloys of the invention shown in Table I, when heat-treated as described for alloys shown in Table IV, are set forth in Table VI.
  • the alloys of this invention also have advantageous characteristics which permit them to be readily fabricated, the characteristic of being adapted to forming by hot working and cold working having been mentioned in regard to some of the foregoing examples of the invention.
  • Brazing is a particularly important process employed in the fabrication of measuring and controlling instruments and other devices in which the alloys of this invention are useful, and it is advantageous that alloys for such instruments and devices be amenable to being brazed by simple methods, i.e., methods requiring neither fluxes nor brazing atmospheres of extreme purity.
  • the alloys of the invention can be readily brazed by simple methods.
  • brazing tests were performed by using a simple method for brazing two alloys of the invention, Alloys ll and 19, and two alloys outside the invention, Alloys 7 A and B, these alloys being of compositions similar to the form of T joints and a very small portion of brazing powder was placed in only one place at the joint, and the success of the test was judged by the flow or wetting action along this joint.
  • the brazing powder was one with a nominal composition including 91.2% nickel, 4.5% silicon, and 2.9% boron, with a melting point (in dry hydrogen) of 17.90l800 F. and a flow point of 1820 F. No flux was used. Tests were run in a dry hydrogen atmosphere with a dew point of approximately 65 F.
  • thermoelastic coemcients approximately equal to any chosen value from minus 50 l0- F. to x l0 F. up to temperatures of at least 600 PI, e.g., 750 F. or l000 F.,which alloys are also characterized by metallurgical stability and high strength up to temperatures of 900 F. or 1000 F.
  • thermoelastic and mechanical characteristics will be advantageous in various different mechanisms and structures in which alloys of the invention will be utilized, it is to be understood that the skilled metallurgist will practice the invention according to the teachings provided herein to provide the thermoelastic and mechanical characteristics most advantageously suited to his particular needs.
  • the composition for the alloys of the invention having a balance index in the range 55.8 to 66.8 provides for consistently obtaining alloys having uniform thermoelastic coefficients which are amenable to controland which are consistently characterized by high inflection temperatures, ferromaguetism, metallurgical stability and high strength, and which can be readily fabricated by casting, working, machining, brazing and welding.
  • alloys in accordance with the invention are uniquely characterized by a controlled thermoelastic coeficient over a temperature range of from room temperature or lower up to about 600 F., or higher, the dis advantages of prior art resilient elements or articles;
  • the present invention is particularly applicable to the production of special resilient metal articles, including springs, pressure sensitive elements, vibratory reeds,
  • the invention is also applicable to the processing of special nickel-cobalt-iron-columbium alloys to develop in these alloys the characteristics of high strength and controlled thermoelasticity.
  • alloys of the invention can contain up to about 6% columbium and/ or up to about 12% tantalum in proportions such that the total of the percent columbium plus one-half the percent tantalum is from about 2.4% to about 6% of the alloy along with nickel, cobalt, iron and titanium in the aforedescribed proportions.
  • the sum of the percent of any columbium plus one-half the percent of tantalum be from about 3% to about 6%, or more advantageously from about 4.5% to about 6%, of the alloy.
  • An age-hardenable alloy consisting essentially of nickel and cobalt proportioned in correlated amounts according to the relationship 1.235 Ni)+% (30:62.2 to 64.8
  • An age-hardenable alloy consisting essentially of nickel and cobalt proportioned in correlated amounts according to the relationship with at least about 16% nickel and at least about 24% cobalt, columbium and tantalum in amounts such that the total of the percent columbium plus one-half the percent tantalum is from about 3% to about 6% of the alloy, with the weight or" tantalum being from about 1% to about 20% of the total weight of columbium and tantalum in the alloy, about 0.5% to about 1.5% titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.1% carbon, less than 1% each of chromium, tungsten and molybdenum, and the balance essentially iron in an amount not less than about 31% of the alloy, said alloy being characterized in the annealed and age hardened condition by a uniform and controllable thermoelastic coeiiicient of absolute value not greater than about 20 10 per degree Fahrenheit up to a temperature of at least about 900 F. and by a
  • columbium and tantalum in amounts such that the total of the percent columbium plus one-half the percent tantalum is from about 2.4% to about 6% of the alloy, with the weight of tantalum being from about 1% to about 20% of the total weight of columbium and tantalum in the alloy, about 0.5% to about 1.5 titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.1% carbon, less than 1% each of chromium, tungsten and molybdenum, and the balance essentially iron in an amoturt not less than about 31% of the alloy, said alloy being characterized in the annealed and age hardened condition by a uniform and controllable thermoelastic coefiicient of absolute value not greater than about 20 10" per degree Fahrenheit up to a temperature of at least about 900 F.
  • An age-hardenable alloy consisting essentially of nickel and cobalt proportioned in correlated amounts according to the relationship 7 1.235 Ni)+% 06:60.4 [0 66.8 r with at least about 16% nickel and at least about 12.5%
  • An age-hardenable alloy consisting essentially of nickel and cobalt proportioned in correlated amounts acabout 1% each cording to the relationship 1.235 Ni)+% 06:60am 66.8 with at least about 16% nickel and at least about 12.5%
  • cobalt, columbium and tantalum in amounts such that the total of the percent columbium plus one-half the perto about of thetotal weight of columbium and tantalum in the alloy, about 0.5 to about 1.5% titanium, up to about 1% each of silicon, manganese and aluminum,
  • said alloy being characterized in the annealed and age.
  • thermoelastic coeflicient of absolute value not greater than about 50x10 per degree Fahrenheit up to a temperature of at 600 F. and by a rupture to about 20% least about 725 F. and by a rupture life of at least 10 hours when subjected to a tensile load of 90,000 pounds per square inch at 900 F.
  • An age-hardenable alloy consisting essentially of nickel and cobalt proportioned in correlated amountsaccording to the relationship 1.235 Ni)-l% Co:55.8 to 60.4
  • An age-hardenable alloy consisting essentially of nickel and cobalt proportioned in correlated amoimtsaccording to the relationship I 1.235 Ni)+% 06:65.8 to 66.8
  • the total of the percent columbium plus one-half the percent tantalum is from about 4.5% to about 6% of the alloy, with the weight of tanalum being from about 1% of the total weight of columbium and tantalum in the alloy, about 0.5% to about 1.5 titanium, up to about 1% each of silicon, manganeseand aluminum, up to about 0.2% carbon, less than 1% each of chromium, tungstenand molybdenum, and the'b'alance essentially iron in an amount not less than about 31% of the alloy, said alloy being characterized in the: annealed and age hardened condition by a uniform and controllable thermoelastic coefficient in the range of from minus 50 10 per degree Fahrenheit to about plus 125 X 10- per degree Fahrenheit up to a temperature of at least about 600 F. and by a rupture life of at least 200 hours when subjected to a tensile load of 90,000 pounds per square inch at 900 F.
  • the Weight of tantalum being from about 1% to about Fahrenheit up to a temperature of at, least about 20% of the total weight of columbium and tantalum in the alloy, about 0.5 to about 1.5% titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.2% carbon, less than 1% each of chromium, tungsten and molybdenum, and the balance essentially iron in an amount not less than about 31% of the alloy, said alloy being characterized in the annealed and age hardened condition by a uniform and controllable thermoelastic co efficient in the range of from minus 50X 10 per degree Fahrenheit to about plus 125 10 er degree Fahrenheit up to a temperature of at least about 600 F. and by a rupture life of at least 25 hours when subjected to a tensile load of 90,000 pounds per square inch at 900 F.
  • columbium and tantalum in amounts such that the total of the percent columbium plus one-half the percent tantalum is from about 2.4% to about 6% of the a lo with the weight of tantalum being from about 1% to about 20% of the total Weight of columbium and tantalum in the alloy, about 0.5 to about 1.5 titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.2% carbon, less than 1% each of chromiurn, tungsten and molybdenum, and the balance essentially iron in an amount not less than about 31% of the alloy, said alloy being characterized in the annealed and age hardened condition by a uniform and controllable thermoelastic coefficient in the range of from minus 50X 10 per degree Fahrenheit to about plus 125 X 10 per degree Fahrenheit up to a temperaure of at least about 600 F. and by a rupture life of at least 10 hours when subjected to a tensile
  • columbium and tantalum in amounts such that the total of the percent columbium plus one-half the percent tantalum is from about 2.4% to about 6% of the alloy, with the weight of tantalum being from about 1% to about 20% of the total weight of columbium and tantalum in the alloy, about 0.5% to about 1.5 titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.2% carbon, less than 1% each of chromium, tungsten and molybdenum, and the balance essentially iron, With the iron content being at least 31% of the alloy.
  • An age-hardenable alloy consisting essentially of nickel and cobalt proportioned in correlated amounts according to the relationship.
  • alloy with at least about 16% nickel and at least about 12.5 cobalt, up to about 6% columbium, up to about 12% tantalum, with the total of the percent columbium plus one-half the percent tantalum being at least about 2.4% but not exceeding about 6% of the alloy, about 0.5% to about 1.5 titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.2% carbon, less than 1% each of chromium, tungsten and molybdenum, and the balance essentially iron in an amount not less than 31% of the alloy, said alloy being characterized in the annealed and age hardened condition by a uniform and controllable thermoelastic coeflicient in the range of from minus 50 10 per degree Fahrenheit to about plus l25 10 per degree Fahrenheit up to a temperature of at least about 600 F. and by a rupture life of at least 10 hours when subjected to a tensile load of 90,000 pounds per square inch at 900 F.
  • alloy with at least about 16% nickel and at least about 24% cobalt, about 4.5% to about 6% columbium, about 0.5% to about 1.5 titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.1% carbon, less than 1% each of chromium, tungsten and molybdenum, and the balance essentially iron in an amount not less than about 31% of the alloy, said alloy being characterized in the annealed and age hardened condition by a uniform and controllable thermoelastic coefiicient of absolute value not greater than about 20 10- per degree Fahrenheit up to a temperature of at least about 900 F. and by a rupture life of at least 200 hours when subjected to a tensile load of 90,000 pounds per square inch at 900 F.
  • alloy with at least about 16% nickel and at least about 12.5 cobalt, about 2.4% to about 6% columbium, about 0.5 to about 1.5 titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.2% carbon, less than 1% each of chromium, tungsten and molybdenum, and the balance essentially iron in an amount not less than about 31% of the alloy, said alloy being charac terized in the annealed and age hardened condition by a uniform and controllable thermoelastic coefiicient in the range of from minus 50 10- per degree Fahrenheit to about plus X 10* per degree Fahrenheit up to a temperature of at least about 600 F. and by a rupture life of at least 10 hours when subjected to a tensile load of 90,000 pounds per square inch at 900 F.
  • nickel and at least about 12.5% cobalt with at least about 16% nickel and at least about 12.5% cobalt, about 2.4% to about 6% columbium, about 0.5% to about 1.5 titanium, up to about 1% each of silicon, manganese and aluminum, up to about 0.2% carbon, less 1% each of chromium, tungsten and molybdenum, and the balance essentially iron, with the iron content being at least 31% of the alloy.
  • a resilient metal article subjected in use to dilfering temperatures within the range of from about minus 320 F. to about 600 F. characterized when in use within said range by ferromagnetism and by a uniform and controlled thermoelastic coefficient not lower than about minus 10 per degree'Fahrenheit and not greater than about x10- per degree Fahrenheit and by a rupture life of at least 10 hours at a stress of 90,000 pounds per square inch at 900 F. and made of an alloy consisting essentially of nickel and cobalt proportioned in correlated amounts according to the relationship 1.235 (%Ni) +%Co 55.8 to 66.8

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US232084A 1962-10-22 1962-10-22 Alloy characterized by controlled thermoelasticity at elevated temperatures Expired - Lifetime US3157495A (en)

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BE639012D BE639012A (fr) 1962-10-22
US232084A US3157495A (en) 1962-10-22 1962-10-22 Alloy characterized by controlled thermoelasticity at elevated temperatures
GB40247/63A GB997767A (en) 1962-10-22 1963-10-11 Age-hardenable alloys
CH1293963A CH426274A (fr) 1962-10-22 1963-10-22 Alliage durcissable par viellissement
SE11570/63A SE302371B (fr) 1962-10-22 1963-10-22

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3630724A (en) * 1968-04-17 1971-12-28 Hitachi Ltd Alloy having a low thermal expansion coefficient and a high spring bending limit
US3871835A (en) * 1969-04-21 1975-03-18 Onera (Off Nat Aerospatiale) Refractory composite alloys containing rod-like and/or platelet-like lamellae
DE2264997A1 (de) * 1971-05-12 1976-03-04 Carpenter Technology Corp Ausscheidungshaertbare nickel-, eisenlegierung
US4006011A (en) * 1972-09-27 1977-02-01 Carpenter Technology Corporation Controlled expansion alloy
US4144102A (en) * 1976-07-08 1979-03-13 The International Nickel Company, Inc. Production of low expansion superalloy products
DE2854002A1 (de) * 1977-12-14 1979-07-12 Wiggin & Co Ltd Henry Hitzebestaendige nickel-stahllegierung
US4190437A (en) * 1977-12-08 1980-02-26 Special Metals Corporation Low thermal expansion nickel-iron base alloy
US4401622A (en) * 1981-04-20 1983-08-30 The International Nickel Co., Inc. Nickel-chromium-iron alloy
US4487743A (en) * 1982-08-20 1984-12-11 Huntington Alloys, Inc. Controlled expansion alloy
US4685978A (en) * 1982-08-20 1987-08-11 Huntington Alloys Inc. Heat treatments of controlled expansion alloy
CN112301255A (zh) * 2020-10-27 2021-02-02 上海交通大学 一种模具用高导热高强Co-Fe-Ni合金及其增材制造方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4445944A (en) * 1981-09-17 1984-05-01 Huntington Alloys, Inc. Heat treatments of low expansion alloys
US4445943A (en) * 1981-09-17 1984-05-01 Huntington Alloys, Inc. Heat treatments of low expansion alloys
DE69216334T2 (de) * 1991-09-19 1997-04-24 Hitachi Metals Ltd Superlegierung mit niedrigem Ausdehnungskoeffizient
KR102048810B1 (ko) 2015-09-29 2019-11-26 히타치 긴조쿠 가부시키가이샤 저열팽창 초내열 합금 및 그의 제조 방법

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2018520A (en) * 1932-03-03 1935-10-22 Westinghouse Electric & Mfg Co High strength alloy
US2044165A (en) * 1932-03-03 1936-06-16 Westinghouse Electric & Mfg Co High strength alloys
US2116923A (en) * 1933-11-01 1938-05-10 Lunkenheimer Co Process of heat-treating alloys
US2773762A (en) * 1949-05-12 1956-12-11 Dubois Ernest Manufacture of unoxidisable timepiece springs

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2018520A (en) * 1932-03-03 1935-10-22 Westinghouse Electric & Mfg Co High strength alloy
US2044165A (en) * 1932-03-03 1936-06-16 Westinghouse Electric & Mfg Co High strength alloys
US2116923A (en) * 1933-11-01 1938-05-10 Lunkenheimer Co Process of heat-treating alloys
US2773762A (en) * 1949-05-12 1956-12-11 Dubois Ernest Manufacture of unoxidisable timepiece springs

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3630724A (en) * 1968-04-17 1971-12-28 Hitachi Ltd Alloy having a low thermal expansion coefficient and a high spring bending limit
US3871835A (en) * 1969-04-21 1975-03-18 Onera (Off Nat Aerospatiale) Refractory composite alloys containing rod-like and/or platelet-like lamellae
DE2264997A1 (de) * 1971-05-12 1976-03-04 Carpenter Technology Corp Ausscheidungshaertbare nickel-, eisenlegierung
DE2223114C3 (de) 1971-05-12 1978-12-14 Carpenter Technology Corp., Reading, Pa. (V.St.A.) Wärmebehandlungsverfahren für eine Legierung auf Nickel-Eisen-Basis
US4006011A (en) * 1972-09-27 1977-02-01 Carpenter Technology Corporation Controlled expansion alloy
US4144102A (en) * 1976-07-08 1979-03-13 The International Nickel Company, Inc. Production of low expansion superalloy products
US4190437A (en) * 1977-12-08 1980-02-26 Special Metals Corporation Low thermal expansion nickel-iron base alloy
DE2854002A1 (de) * 1977-12-14 1979-07-12 Wiggin & Co Ltd Henry Hitzebestaendige nickel-stahllegierung
US4200459A (en) * 1977-12-14 1980-04-29 Huntington Alloys, Inc. Heat resistant low expansion alloy
US4401622A (en) * 1981-04-20 1983-08-30 The International Nickel Co., Inc. Nickel-chromium-iron alloy
US4487743A (en) * 1982-08-20 1984-12-11 Huntington Alloys, Inc. Controlled expansion alloy
US4685978A (en) * 1982-08-20 1987-08-11 Huntington Alloys Inc. Heat treatments of controlled expansion alloy
CN112301255A (zh) * 2020-10-27 2021-02-02 上海交通大学 一种模具用高导热高强Co-Fe-Ni合金及其增材制造方法
CN112301255B (zh) * 2020-10-27 2021-07-30 上海交通大学 一种模具用高导热高强Co-Fe-Ni合金及其增材制造方法

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BE639012A (fr)
SE302371B (fr) 1968-07-15
GB997767A (en) 1965-07-07
CH426274A (fr) 1966-12-15

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