US3262823A - Maraging steel - Google Patents

Maraging steel Download PDF

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US3262823A
US3262823A US286365A US28636563A US3262823A US 3262823 A US3262823 A US 3262823A US 286365 A US286365 A US 286365A US 28636563 A US28636563 A US 28636563A US 3262823 A US3262823 A US 3262823A
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alloys
steel
present
plate
strength
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Edward P Sadowski
Raymond F Decker
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Huntington Alloys Corp
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International Nickel Co Inc
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Priority to US286365A priority Critical patent/US3262823A/en
Priority to GB22124/64A priority patent/GB1013778A/en
Priority to FR977090A priority patent/FR1398259A/fr
Priority to AT479964A priority patent/AT259606B/de
Priority to CH735964A priority patent/CH443699A/fr
Priority to BE648899D priority patent/BE648899A/xx
Priority to NL6406429A priority patent/NL6406429A/xx
Priority to LU46265D priority patent/LU46265A1/xx
Priority to DEJ25991A priority patent/DE1239109B/de
Priority to ES300688A priority patent/ES300688A1/es
Priority to DK283764AA priority patent/DK105050C/da
Application granted granted Critical
Publication of US3262823A publication Critical patent/US3262823A/en
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    • 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
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
    • 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
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/54—Ferrous alloys, e.g. steel alloys containing chromium with nickel with boron

Definitions

  • the present invention relates to high strength steel and, more particularly, to an exceedingly tough, controlled, high strength maraging steel especially usable as plate and as welded structures made from said plate.
  • Heat treatment problems are only some of the many difficulties which must be considered by an engineer designing a structure to be formed from plate.
  • Weight and buoyancy considerations often require the designer to specify a steel of controlled high strength, i.e., a steel having a yield strength of about 140,000 pounds per square inch (p.s.i.) up to about 200,000 -p.s.i.
  • p.s.i. pounds per square inch
  • the steel to be specified as plate must be weldable without heat affected zone (H.A.Z.) cracking under conditions encountered in the practical construction of large structures.
  • the difference between the energy absorption of transverse and longitudinal specimens can be of the order of 100% and higher based upon the transverse impact value.
  • the difference between the C.V.N. impact values in foot-pounds (ft.-lbs.) of transverse and longitudinal specimens of S.A.E. Steel No. 8617 taken at 0 F. is at least about 50 ft.-lbs.
  • This difference is about 200% of the maximum C.V.N. impact value of 25 ft.-lbs., exhibited by transverse specimens of this steel at 0 F. with a hardness of 30 Rockwell C units (R Uniformly, in the 15 graphical representations set forth on pages 230 and 231 of the Metals Handbook, the C.V.N.
  • plate-structure designing and, in particular, specifying alloys for plate structures is a very complex activity.
  • the metallurgical art has never provided the designer with a wholly satisfactory commercial steel of controlled high strength suitable for use in plate structures adapted to be subjected in use to high pressures and violent impacts at temperatures from above room temperature down to about 100 F. and lower.
  • cordance with the present invention include, with respect It has now been discovered that an alloy steel conto alloy composition, alloys containing about 11% to taining specially controlled and interrelated amounts of about 12% nickel and/or about 3% to about 5% chromialloying elements is especially suited for use in the manuum and/ or about 2.5% to about 3.5% molybdenum, and/ facture of plate structures having a high strength to or about 0.05% to about 0.15% aluminum and/or about weight ratio. 0.20% to about 0.30% aluminum.
  • FIGURE 1 of the drawing shows It is a further object of the invention to provide novel that as the aluminum content of alloys in accordance with welded plate structures made from said novel steel.
  • the invention (containing nominally 12% nickel, 5%
  • the invention further contemplates providing a novel chromium and 3% molybdenum) is increased from 0.1% process of producing said novel plate structures. to about 0.3%, the yield strength of the alloys increases
  • the Charpy V-Notch impact values at 70 F. from the following description taken in conjunction with decrease only slightly.
  • the accompanying drawing in which: the impact values tend to decrease at an increasingly FIGURE 1 is a graphical representation of mechanical rapid rate to totally unacceptable levels. Consequently, characteristics of a typical steel of the present invention it is important to specially maintain the amount of alumias related to the aluminum content of the alloy; and mum in the alloys of the invention below an ultimate FIG.
  • manganese up to not more than 0.25% manganese, up to about 0.50% silicon can be tolerated in alloys of the about 0.30% silicon, up to about 0.01% boron, up to present invention provided that the aluminum copresent about 0.1% zirconium, with the balance being essentially with amounts of silicon in excess of about 0.30% be no iron in a amount of at least about 74%.
  • the alloys greater than about 0.30%. can also contain impurities and incidental elements in The alloy ranges set forth in Table I are illustrative small amounts which do not deleteriously affect the of the broadly stated and more advantageous alloy ranges basic and novel characteristics of the alloy. Impurities of nickel, chromium, molybdenum, titanium and alumisuch as sulfur, phosphorous, hydrogen, oxygen, nitrogen num as set forth hereinbefore.
  • Incidental elements such as cobalt and copper are not specifically beneficial in the alloys of the present invention and should be limited to those small amounts which are unavoidably introduced into the composition during commercial manufacture. Small amounts of elements such as beryllium, vanadium, columbium, tantalum and tungsten can be employed in the alloys of the present invention.
  • alloys in accordance with the present invention have, at normal temperatures of usage, essentially a martensitic structure, that is, a structure resulting from a low temperature (below about 700 F.), substantially diffusionless transformation from austenite.
  • the alloys increase in hardness, for example, from about 25 R to between about 33 R and about 43 R.
  • This hardening response during aging distinguishes the alloys of the present invention from substantially all known prior art carbon steels (i.e., steels containing more than about 0.1% carbon) in that or 2% tungsten.
  • prior art carbon steels exhibit a softening response.
  • the alloys of the present invention are heat treated by a process which includes a first transformation to martensite after hot working, a solution anneal at a temperature in excess of about 1400 F., a second transformation to martensite following said solution anneal, and a final aging treatment in the vicinity of about 900 F. for a time in excess of about 1 hour and up to about hours to harden and strengthen the alloy.
  • the transformation to martensite can be accomplished by merely cooling the alloys to a temperature below about 150 F. The rate of cooling is not critical and drastic quenching operations are definitely not needed in order to obtain the advantageous mechanical characteristics of the alloys of the present invention.
  • alloys according to the present invention are made by conventional high strength steel melting practice.
  • alloys of the present invention can be made by melting together relatively pure iron, nickel, chromium and molybdenum; decarburizing the resultant molten metal to produce a carbon level below about 0.03% by weight; deoxidizing the decarburized molten metal with silicon and manganese so as to limit residual silicon and especially residual manganese in the metal to within the aforementioned ranges for these elements; completing deoxidation by adding aluminum and titanium to provide residual amounts within the aforementioned ranges of aluminum and titanium; adding any desired boron and/ or zirconium and casting the metal into ingots.
  • the alloys can be melted in high frequency induction furnaces advantageously under a blanket of inert gas such as argon. Alternatively, vacuum melting can be employed. Selected scrap can be used in the manufacture of alloys of the present invention provided proper basic electric furnace practice is employed and oxygen lancing is used to reduce carbon to levels below about 0.03%.
  • the ingots are subjected to hot working operations at starting temperatures of about 2300 F., to mechanically homogenize the as-cast therein.
  • the cooled alloys can be worked further by hot-cold working and/or cold working to sheet thicknesses.
  • the alloy is usually annealed at temperatures of about 1450 F. to about 1900 F. for about one to about four hours.
  • the result of the annealing (or solution) treatment is to retransform any martensite to austenite, to place substantially all the alloying elements in solution in the matrix of the alloy and to remove the residual elfects of hot and cold work.
  • the alloy is cooled to room temperature or to a temperature at least below about 150 F.
  • the rate of cooling after annealing is not critical but it is preferred to cool at a rate at least equal to the rate of air cooling.
  • the alloy structure changes from austenite (face-centered cubic) to martensite (bodycentered cubic) by means of an essentially diffusionless process.
  • the annealed martensitic alloy has a hardness of about 25 R Cold working, as mentioned hereinbefore, can be performed on the annealed martensitic alloy to the extent equivalent to about reduction by rolling.
  • the annealed martensitic alloy of the present invention can be readily machined by sawing, drilling, turning, planing, milling and the like to final dimension. During subsequent aging, there is extremely little dimensional change.
  • the annealed martensitic alloy After the annealed martensitic alloy has been formed or machined into the desired configuration, it is aged for about one to about ten hours at temperatures of about 800 F. to about 1000 F. A practical and recommended aging treatment is heating for about 3 hours at 900 F.
  • samples of the annealed martensitic alloy increased in hardness from a level in the range of about 25 R, to about 32 R in the annealed condition up to a level in the range of about 33 to 43 R in the aged condition.
  • the yield strength of the aged alloys is of the order of about 140,000 p.s.i. to about 190,000 p.s.i. or even to about 200,000 p.s.i.
  • the yield strength (Y.S.) level of aged samples of the alloy types disclosed in Table I are set forth in Table II:
  • Bal. means balance iron, inclusive of small amounts of silicon, boron, zirconium and/0r calcium together with amounts of phosphorus below about 0.007% and sulfur below about 0.004%.
  • Alloy No. 7 contains 0.48% silicon.
  • Hot worked alloys are cooled to room temperature or at least below tensitic and age hardened condition the best combination of room temperature strength (as measured by yield strength) and room temperature toughness (as measured about F. to induce a martensitic transformation 75 by C.V.N. values obtained with transverse specimens from The alloys set forth in Table III, exhibit in the marrolled plate). Additional examples of alloys in accordance with the present invention are set forth in Table IV:
  • Alloy N0. 12 contains 0.31% silicon.
  • the alloys were then 3L0 5 subjected to a solution treatment (annealing) at 1500 F. 31:2 25:3 for 1 hour followed by cooling to room temperature to effect a second transformation to martensite.
  • the alloys Annealed for 1 11011! at 1500 R followed y r were then aged for 3 hours at 900 F. Hardnesses before and after aging are set forth in Table V:
  • the data set forth in Table V demonstrates that during aging at temperatures of about 800 F. to about 1000 F., the martensitic alloys of the present invention increase in hardness by up to about 15 Rockwell C units. After aging, the martensitic alloys of the present invention exhibit mechanical characteristics as set forth in Table VI.
  • alloys of the present invention also exhibit excellent notch tensile strengths of the order of 1.5 (or greater) times the ultimate tensile strength. It is also characteristic of alloys of the present invention that the ratios of yield strength to ultimate tensile strength are in excess of 0.9 and usually in excess of 0.95.
  • alloys in accordance with the present invention In the as-annealed condition, i.e., after solution treatment at 1500 F. for 1 hour, followed by air cooling, alloys in accordance with the present invention also exhibit an excellent combination of characteristics.
  • Table VIA illustrates this with respect to alloys containing, in addition to the indicated aluminum percentages, nominally about 12% nickel, chromium, 3% molybdenum, about 0.01% carbon, with the balance being essentially iron.
  • weld-affected areas of aged martensitic alloys of the present invention can be restored in properties by a simple postweld heat treatment at about 900 F.
  • a simple postweld heat treatment can be applied to a large Welded plate structure by means, for example, of strip heaters, electrical resistance heating, induction heating, torch heating, etc.
  • Macro and micro examinations of the weld-affected areas of welded plate samples disclosed only sound metal with no discernible cracks.
  • heat affected zones of the metal of the welded samples softened somewhat.
  • Subsequent trnaraging resulted in complete restoration to the hardness of the plate body.
  • cruciform Welding tests embodying a high degree of restraint no cracking was discernible in heat affected zones of 1 inch plate samples in accordance with the present invention.
  • the chemical composition of the alloys of the present invention be maintained within the Both chromium and molybdenum within the ranges of about 2.5% to 5.5% and about 2% to about 4%, respectively, are advantageous because with amounts of these elements lower than those specified, alloys of much lower strength are attained.
  • Increasing the amounts of molybdenum above those specified as a maximum results in drastically lowering the toughness of the alloys and lowering strength.
  • An excessive amount of chromium in the alloy tends to lower strength. Amounts of chromium in excess of about 5.5% and up to about 8% can be advantageous from a corrosion standpoint.
  • Amounts of manganese above about 0.25% which are normally considered as beneficial in good alloy steel manufacturing practice, are detrimental to the toughness of the alloys of the present invention and, accordingly, the maximum manganese permitted in the alloys of the present invention is about 0.25%. It is essential that in the presently disclosed alloys the carbon be kept at a maximum of about 0.03%, i.e., less than 0.033%. Amounts of carbon even slightly in excess of 0.033% have a deleterious effect on toughness of the alloys. Raising carbon in the alloys of the present invention to very (comparatively speaking) high levels of 0.1% or more, results in the production of alloys akin to known carbon steels, said alloys having the defects and deficiencies of carbon steels as discussed in detail herein before.
  • the maximum specified carbon content is also highly critical in that the deleterious effects of amounts in excess of about 0.03% in the alloys of the invention cannot be remedied by the use of carbide formers such as titanium.
  • carbide formers such as titanium.
  • metal carbides such as titanium carbide, drastically reduce the toughness of alloys which oth erwise would be within the ambit of the present invention.
  • Amounts of aluminum up to about 0.3% or 0.4% assist in strengthening the alloys of the present invention as shown in FIGURE 1 of the drawing.
  • Titanium in amounts up to about 0.3%, e.g., about 0.1% to about 0.2%, in combination with less than about 0.03% carbon is advantageous in that it tends to minimize the deleterious effects of small amounts of sulfur which may inadvertently be present in the alloys.
  • compositions of alloys (designated by letters) outside the present invention are set forth in Table IX together with compositions of alloys (designated by munbers) within the present invention to provide a comlimits of the ranges set forth hereinbefore.
  • Bal. means balance iron, inclusive of small amounts of silicon, boron, zirconium and/or calcium, together with amounts of phosphorus below about 0.007% and sulfur below about 0.004%.
  • FIG. 2 of the drawing shows the interrelation between 0.2% yield strength and room temperature (70 F.) Charpy V-Notch impact strengths of alloys set forth in the present specification. It is known in general for steels that there is an inverse relationship between strength and toughness. Thus, for any given steel as the strength is increased, the toughness decreases. For alloys in accordance with the present invention containing alloying elements within the ranges set forth in Table IX, this inverse relationship is generally representable by approximately the curve DE as shown in FIG. 2.
  • the curves AB and BC effectively define the minimum strength and toughness limits obtainable.
  • Such alloys can be represented by a point lying above and to the right of curves AB and BC when heat treated in accordance with the presently disclosed process to 0.2% yield strengths of about 140 k.s.i. to about 200 k.s.i.
  • 0.2% yield strengths As a general approximation, such alloys are characterized by 0.2% yield strengths and room temperature C.V.N. impact strengths such that both of the following quasi-mathematical criteria are satisfied:
  • alloying elements in accordance with the present invention include certain interrelationships among alloying elements.
  • One of the essential concepts of the present invention is that in alloys in accordance with the invention, the total nickel plus chromium content must be between about 13.5% and about 19%.
  • nickel and. chromium are copresent in the alloys of the present invention in the amounts set forth hereinbefore, these elements appear to interact during maraging (i.e., aging in the martensitic condition after martensitic transformation), to harden and strengthen the alloy.
  • the nickel content is about 11% to about 12%
  • the chromium content is about 3% t0 about and the total of the nickel plus chromium is about 14% to about 16%.
  • the present invention is particularly applicable to the provision of plate for high strength, welded structures.
  • Examples of such structures are ships hulls, pressure vessels for chemical reactors and high pressure equipment, rotors for electrical generators, etc.
  • the alloys of the present invention can, of course, be provided in forms other than plate, for example, sheet, bar, rod, wire, strip, tube and the like. These forms can be produced by hot working, e.g., forging, rolling, extrusion and the like, cold working, e.g., trolling, drawing, pressing, etc., hotcold working, machining including turning, drilling, milling and the like and, in general, by any conventional shaping or cutting operation used in ferrous metal technology.
  • the alloys of the present invention can be formed by any of the relatively new high-energy processes, including high-energy impact processes and explosive forming.
  • the alloys of the present invention can also be provided with a hard surface by conventional low temperature nitriding.
  • the present invention provides a novel maraging steel having in the age hardened condition highly useful levels of strength in excess of about 140 k.s.i. yield strength coupled with high levels of toughness indicated by C.V.N. impact values in transverse plate samples at room temperatures in excess of about 70 ft.- lbs. at yield strengths up to about 150 k.s.i. and in excess of about 50 ft.-lbs. at yield strength-s up to about 170 k.s.i. or higher.
  • This advantageous combination of strength and toughness is highly useful since it can be readily attained in welded plate structures.
  • the alloys also exhibit advantageous combinations of mechanical characteristics at cryogenic temperatures. For example, in general the alloys of the present invention exhibit C.V.N.
  • Other metals such as alloy carbon steels cannot, under commercial conditions, attain the required strength and toughness combination in welded plate structures without resorting to uneconomical and/ or technically impractical preand/or postweld heat treatments.
  • a maraging steel for use at 0.2% yield strengths in excess of about 140,000 pounds per square inch in thick sections in plate structures consisting essentially, in weight percent, of about 9.5% to about 13.5% nickel, about 2.5% to about 8% chromium, said nickel and said chromium being interrelated so that the sum thereof is about 13.5% to 19%, about 1.9% to about 4.2% molybdenum, about 0.05% to about 0.40% aluminum, up to about 0.3% titanium, about 0.001% to about 0.03% carbon, up to about 0.25% manganese, up to about 0.50% silicon with the silicon content not exceeding about 0.3% when the aluminum exceeds about 0.3%, up to about 0.01% boron, up to about 0.1% zirconium, up to about 2% total of metal from the group consisting of beryllium, vanadium, columbium, tantalum and tungsten, said elements in said group being present individually in 14 amounts of 0% to 0.2% beryllium, 0% to 1% vanadium, 0% to 0.4% columbium,
  • a steel as in claim 1 heat treated by subjecting said steel to a first martensitic transformation, annealing said steel to convert the thus-formed martensite to austenite, cooling the annealed steel to effect a second transformation to martensite and thereafter aging the thus-treated martensitic steel at about 800 F. to about 1000 F. to increase the 0.2% yield strength thereof to at least about 140,000 pounds per square inch.
  • a maraging steel for use at 0.2% yield strengths in excess of about 140,000 pounds per square inch in thick sections in plate structures consisting essentially, in weight percent, of about 9.5% to about 13.5% nickel, about 2.5% to 5.5% chromium, said nickel and said chromium being interrelated so that the sum thereof is about 13.5% to 17%, about 1.9% to about 4.2% molybdenum, about 0.05% to about 0.40% aluminum, up to about 0.3% titanium, about 0.001% to about 0.03% carbon, up to about 0.25 manganese, up to about 0.50% silicon with the silicon content not exceeding about 0.3% when the aluminum exceeds about 0.3%, up to about 0.01% boron, up to about 0.1% zirconium, up to about 2% total of metal from the group consisting of beryllium, vanadium, columbium, tantalum and tungsten, said elements in said group being present individually in amounts of 0% to 0.2% beryllium, 0% to 1% vanadium, 0% to 0.4% columbium, 0% to
  • a maraging steel as in claim '5 containing about 11% to about 12% nickel and about 2.5% to about 3.5% molybdenum.
  • a maraging steel for use at 0.2% yield strengths in excess of about 140,000 pounds per square inch in thick sections in plate structures consisting essentially, in weight percent, of about 9.5% to about 13.5% nickel, about 2.5% to about 5.5% chromium, said nickel and said chromium being interrelated so that the sum thereof is about 14% to about 16%, about 1.9% to about 4.2% molybdenum, about 0.05% to about 0.40% aluminum, up to about 0.3% titanium, up to about 0.03% carbon, up to about 0.15% manganese, up to about 0.3% silicon with the balance being essentially iron.
  • a process of heat treating maraging steel containing about 9.5% to about 13.5% nickel, about 2.5% to 5.5% chromium, about 1.9% to about 4.2% molybdenum, about 0.05% to about 0.4% aluminum and less than about 0.03% carbon comprising subjecting said steel to a first martensitic transformation, annealing said steel to convert the thus-formed martensite to austenite, cooling the annealed steel to effect a second transformation to martensite and thereafter aging the thus-treated martensitic steel at about 800 F. to about 1000 F. for about 1 to about 10 hours.
  • a maraging steel for use at 0.2% yield strengths in excess of about 140,000 pounds per square inch in thick sections in welded plate structures consisting essentially, in weight percent, of about 11% to about 12% nickel, about 2.5% to about 5% chromium, said nickel and said chromium being interrelated so that the sum thereof is about 14% to about 17%, about 1.9% to about 4.2% molybdenum, about 0.05% to about 0.2% aluminum, up to about 0.3% titanium, about 0.001% to 0.033% carbon, up to about 0.2% manganese, up to about 0.25% silicon, up to about 0.01% boron, up to about 0.1% zirconium, with the balance being essentially iron.
  • a maraging steel consisting essentially, in weight References Cited by the Examiner percent, of about 10% to about 12.5% nickel, about 3% to about 5.5% chromium, the total of said nickel and said UNITED STATES PATENTS chromium being at least about 14%, about 2% to about 2999039 9/1961 Lula et 14837 4% molybdenum, about 0.05% to about 0.3% aluminum, 5 3,093,519 6/1963 Decker et 148-442 X about 0.1% to about 0.2% titanium, up to about 0.03% 3,123,506 3/1964 Tanclyn 14831 carbon, up to about 0.25% manganese, up to about 0.3% 3,151,978 10/1964 Perry et a1 148 37 silicon, with the balance being essentially iron. 3,164,497 1/1965 Matsuda 148-142 11.
  • a maraging steel as in claim 10 containing about DAVID RECK Exammer' 2.5% to about 3.5% molybdenum.

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  • Engineering & Computer Science (AREA)
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  • Heat Treatment Of Steel (AREA)
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US286365A 1963-06-07 1963-06-07 Maraging steel Expired - Lifetime US3262823A (en)

Priority Applications (11)

Application Number Priority Date Filing Date Title
US286365A US3262823A (en) 1963-06-07 1963-06-07 Maraging steel
GB22124/64A GB1013778A (en) 1963-06-07 1964-05-28 Alloy steel
AT479964A AT259606B (de) 1963-06-07 1964-06-04 Martensitischer Chrom-Nickel-Stahl und Verfahren zu seiner Wärmebehandlung
FR977090A FR1398259A (fr) 1963-06-07 1964-06-04 Acier allié
BE648899D BE648899A (es) 1963-06-07 1964-06-05
NL6406429A NL6406429A (es) 1963-06-07 1964-06-05
CH735964A CH443699A (fr) 1963-06-07 1964-06-05 Acier martensitique
LU46265D LU46265A1 (es) 1963-06-07 1964-06-06
DEJ25991A DE1239109B (de) 1963-06-07 1964-06-06 Verwendung einer martensitaushaertbaren Stahllegierung als Werkstoff fuer druck- undschlagfeste Gegenstaende
ES300688A ES300688A1 (es) 1963-06-07 1964-06-06 Mejoras introducidas en la fabricación de aceros martensíticos
DK283764AA DK105050C (da) 1963-06-07 1964-06-06 Martensitisk stål især til svejste pladekonstruktioner og fremgangsmåde til varmebehandling heraf.

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BE (1) BE648899A (es)
CH (1) CH443699A (es)
DE (1) DE1239109B (es)
DK (1) DK105050C (es)
ES (1) ES300688A1 (es)
FR (1) FR1398259A (es)
GB (1) GB1013778A (es)
LU (1) LU46265A1 (es)
NL (1) NL6406429A (es)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3342590A (en) * 1964-09-23 1967-09-19 Int Nickel Co Precipitation hardenable stainless steel
US3347663A (en) * 1964-09-23 1967-10-17 Int Nickel Co Precipitation hardenable stainless steel
US3475164A (en) * 1966-10-20 1969-10-28 Int Nickel Co Steels for hydrocracker vessels containing aluminum,columbium,molybdenum and nickel
US3715231A (en) * 1971-05-28 1973-02-06 Us Army Storage of liquid hydrazine rocket fuels
US4125260A (en) * 1976-05-17 1978-11-14 True Temper Corporation Tubular golf shaft of stainless steel
US4579590A (en) * 1983-03-16 1986-04-01 Mitsubishi Jukogyo Kabushiki Kaisha High strength cobalt-free maraging steel
US20150053697A1 (en) * 2013-08-22 2015-02-26 Autoliv Asp, Inc. Double swage airbag inflator vessel and methods for manufacture thereof
CN113462978A (zh) * 2021-06-30 2021-10-01 重庆长安汽车股份有限公司 一种汽车用超高强度马氏体钢及轧制方法
US11286534B2 (en) 2018-07-18 2022-03-29 The Boeing Company Steel alloy and method for heat treating steel alloy components

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999039A (en) * 1959-09-14 1961-09-05 Allegheny Ludlum Steel Martensitic steel
US3093519A (en) * 1961-01-03 1963-06-11 Int Nickel Co Age-hardenable, martensitic iron-base alloys
US3123506A (en) * 1964-03-03 Alloy steel and method
US3151978A (en) * 1960-12-30 1964-10-06 Armco Steel Corp Heat hardenable chromium-nickel-aluminum steel
US3164497A (en) * 1963-02-08 1965-01-05 North American Aviation Inc Progressive slope aging process

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US3342590A (en) * 1964-09-23 1967-09-19 Int Nickel Co Precipitation hardenable stainless steel
US3347663A (en) * 1964-09-23 1967-10-17 Int Nickel Co Precipitation hardenable stainless steel
US3475164A (en) * 1966-10-20 1969-10-28 Int Nickel Co Steels for hydrocracker vessels containing aluminum,columbium,molybdenum and nickel
US3715231A (en) * 1971-05-28 1973-02-06 Us Army Storage of liquid hydrazine rocket fuels
US4125260A (en) * 1976-05-17 1978-11-14 True Temper Corporation Tubular golf shaft of stainless steel
US4579590A (en) * 1983-03-16 1986-04-01 Mitsubishi Jukogyo Kabushiki Kaisha High strength cobalt-free maraging steel
US20150053697A1 (en) * 2013-08-22 2015-02-26 Autoliv Asp, Inc. Double swage airbag inflator vessel and methods for manufacture thereof
US9776592B2 (en) * 2013-08-22 2017-10-03 Autoliv Asp, Inc. Double swage airbag inflator vessel and methods for manufacture thereof
US11286534B2 (en) 2018-07-18 2022-03-29 The Boeing Company Steel alloy and method for heat treating steel alloy components
CN113462978A (zh) * 2021-06-30 2021-10-01 重庆长安汽车股份有限公司 一种汽车用超高强度马氏体钢及轧制方法
CN113462978B (zh) * 2021-06-30 2022-12-09 重庆长安汽车股份有限公司 一种汽车用超高强度马氏体钢及轧制方法

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CH443699A (fr) 1967-09-15
BE648899A (es) 1964-12-07
NL6406429A (es) 1964-12-08
FR1398259A (fr) 1965-05-07
GB1013778A (en) 1965-12-22
AT259606B (de) 1968-01-25
ES300688A1 (es) 1964-12-01
LU46265A1 (es) 1964-12-05
DK105050C (da) 1966-08-08
DE1239109B (de) 1967-04-20

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