US3578440A - Nickel-copper alloy - Google Patents

Nickel-copper alloy Download PDF

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Publication number
US3578440A
US3578440A US715898A US3578440DA US3578440A US 3578440 A US3578440 A US 3578440A US 715898 A US715898 A US 715898A US 3578440D A US3578440D A US 3578440DA US 3578440 A US3578440 A US 3578440A
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United States
Prior art keywords
alloy
nickel
machinability
hours
inch
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Expired - Lifetime
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US715898A
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English (en)
Inventor
Herbert L Eiselstein
Carl B Haeberle
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Huntington Alloys Corp
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International Nickel Co Inc
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Publication date
Application filed by International Nickel Co Inc filed Critical International Nickel Co Inc
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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
    • C22C19/002—Alloys based on nickel or cobalt with copper as the next major constituent

Definitions

  • the machining problem has been a vexing problem in connection with the alloy and, despite many efforts, no commercially feasible improvement in machinability has been discovered.
  • one expedient which has been found actually to improve machinability of the alloy to a marked extent has been an anneal at a high temperature, e.g., 2100 F. or higher.
  • a high temperature e.g. 2100 F. or higher.
  • heat treatment at a high enough temperature to provide an improvement in machinability of the alloy resulted in production of extremely large grains, a condition which could not be tolerated in commercial practice.
  • the present invention comprises an age hardenable nickel-copper alloy containing not more than 0.10% carbon, e.g., about 0.03% to about 0.10% carbon, not more than 0.5% titanium, e.g., about 0.1% or about 0.2% to about 0.5% titanium, about 2.5 to about 3.5% aluminum, about 63% to about 70% nickel and the balice ance, with the exception of incidental elements and impurities, being essentially copper.
  • a preferred alloy in accord ance with the invention nominally contains about 0.07% carbon, about 0.3% titanium, about 3% aluminum, about 63% to about 70% nickel and the balance essentially copper.
  • the carbon content is controlled within the range of about 0.03% to about 0.10%, and the titanium content is controlled so as not to exceed 0.5 to confer weldability and machinability to the alloy while at the same time enabling the production of high strength therein upon aging.
  • the aluminum is maintained in the range of about 2.5 to about 3.5% to permit production of high properties upon aging the alloy.
  • the alloy may contain small amounts of incidental elements which do not materially affect the basic and novel characteristics of the alloy including up to about 2% iron, up to about 1.5% manganese, and up to about 0.5 silicon.
  • sulfur is an undesirable impurity and should not exceed 0.010% while phosphorus should not exceed about 0.02%.
  • the boron content should not exceed 0.01%.
  • the alloy is age hardened by heating to a temperature in the range of about 1100 F. to about 1225" F. and then slowly cooling, e.g., at a rate of 25 F. per hour or less, the alloy to a temperature of about 900 F.
  • the alloy can be held successively at temperatures of about 1150 F., 1050 F. and 950 F. for periods of up to about 8 hours at each temperature and with furnace cooling between each step.
  • the alloy displays a maximum rate of hardening at about 1150 F.
  • a preferred particularly satisfactory heat treatment comprises a heating at about 1150 F. for about 2 to about 8 hours, e.g., 2 hours, furnace cooling to 1050 F., holding for about 2 to about 6 hours, e.
  • Hot finished and aged, e.g., hot rolled and aged or forged and aged products will provide a yield strength (0.2% offset) of at least 80,000 pounds per square inch (p.s.i.), a tensile strength of at least 130,000 psi. and an elongation of at least 20% measured over a gage length four times the specimen diameter.
  • the alloy is solution treated or annealed at temperatures in the range of about 1350 F. to about 1400 for times on the order of about /z hour, al though shorter annealing times, even as short as five minutes can be employed in the case of cold worked materials, e.g., rod, wire, strip, sheet, tubing, etc., with the higher annealing temperatures.
  • the low solution or annealing temperature is a further important advantage of the alloy in that oxidation, distortion, grain growth and thermal shock effects are reduced or eliminated as compared to the case wherein higher annealing temperatures are used. Higher annealing temperatures and shorter times, e.g., about 1600 F.
  • the alloy is immune to strainage cracking after welding and, in addition, that the machinability of the alloy in all conditions of working and heat treatment is excellent.
  • the material produces a long, stringy chip in machining and surface finish of machined pieces is excellent.
  • Horsepower requirements for cutting the alloy are about the same as those for the known free machining stainless steel AISI Type 303 (Se), i.e., about 0.7 to about 0.8 horsepower per cubic inch of metal removed per minute.
  • best machinability is manifested when the alloy is machined in the annealed condition. This factor promotes the desired practice in conjunction with age hardenable alloys of machining the alloy almost to finish size before hardening followed by finished machining after hardening.
  • a commercial scale electric arc furnace air melt was produced and cast into inch x 2.0 inch x 90 inch ingots.
  • the alloy contained 65.37% nickel, 3% aluminum, 0.07% carbon, 0.84% iron, 0.54 manganese, 0.11% silicon, 0.30% titanium, 0.009% sulfur and the balance copper.
  • One ingot was hot rolled to a 4-inch diameter round without difliculty.
  • a portion of the material was cold drawn to 3 /8 inch diameter rod while another portion was forged into a 2-inch square and a further portion was further worked into the form of 4- inch diameter cold drawn rod.
  • the resulting: material was subjected toroom temperature tensile testing in various conditions, including as-rolled, as-drawn, annealed and aged conditions with the results set forth in the following Table II in which the term annealed indicates a heat treatment at 1400 F. for /2 hour and the term aged indicates a heat treatment comprising heating at 1150 F. for 2 hours, furnace cooling to 1050" F. and hold for 4 hours (2 hours where symbol (A) appears), furnace cooling to 950 F. and hold for 4 hours followed by air cooling to room temperature.
  • V X 100 standard condition (V Using the hot rolled, annealed (1400 F. /2 hour) condition as standard, the comparisons are shown in the following Table I:
  • the tool material employed was a tungsten-titanium carbide material with a cobalt binder.
  • the tool was cut with a back rake angle of 0, a side rake angle of 5, an end clearance angle of 5, a side clearance angle of 5, an end cutting edge angle of 15, a side cutting edge angle of 15 and a nose radius of inch.
  • the cutting site was flooded with a commercial coolant.
  • a feed rate of 0.00825 inch per revolution with a depth of cut of 0.050 inch was employed in the test.
  • a tool life end point was taken as 0.015 inch flank wear. Excellent surface finish was observed in the testing.
  • the machinability data was plotted in uniform straight lines and no tendency toward erratic behavior was observed.
  • the ordinate values are very high, further indicating excellent machinability.
  • the mill condition, e.g., hot rolled and annealed, in which the alloy was subjected to the machinability test is indicated on the tool life lines in the drawmg.
  • the welded nickel-copper alloy assembly was then cut from the strongback and the weld was sliced for examination. No strainage or underbed cracking was observed and side bend tests in which Aa-inch thick transverse slices cut through the weld were bent about a 1 /2 inch diameter pin indicated there were no fissures or voids in the weld area.
  • the tensile properties of the aged weld material were determined by means of transverse tensile tests produced from tensile specimens, including the weld, together with all weld metal tests. The results are set forth in the following Table III:
  • the machinability level with carbide tools was lower than that of high speed steel tools.
  • the tool life line had a reverse curve at a very low machinability level indicating a highly undesirable condition as shown by Curve A in the drawing for cold drawn, as-drawn material made of the alloy.
  • Curve B in the drawing is the tool life line for cold drawn, aged material made of this alloy outside of the invention.
  • the alloy provided in accordance with the invention is characterized by high strength, toughness and ductility over a wide range of temperatures and is useful over the temperature range from minus 423 F. to about 800 F.
  • the alloy may be fabricated into such articles as pump shafts and impellers, propellor shafts, oil well drill c01- lars and instruments, doctor blades and scrapers, valve trim, springs, etc.
  • the alloy is readily produced in any of the common mill forms, including rod, bar, sheet, strip, tubing, extruded shapes, forgings, etc.
  • An age hardenable alloy having improved machinability and weldability in wrought form consisting essentially of about 63% to about nickel, about 2.5% to about 3.5% aluminum, about 0.07% carbon, about 0.3% titanium, not more than about 2% iron, not more than about 1.5% manganese, not more than about 0.5% silicon, not more than about 0.010% sulfur and the balance essentially copper.
  • the improvement in compositional control therefor to provide enhanced machinability and freedom from weld cracking while retaining high strength in the aged condition which comprises controlling the carbon content in the range of about 0.07% the titanium content in the range of about 0.3% the aluminum content in the range of about 2.5% to about 3.5%, the nickel content in the range of about 63% to about 70% and with the balance essentially copper.
  • the process for age hardening an alloy consisting essentially of about 63% to about 7 0% nickel, about 2.5 to about 3.5% aluminum, about 0.03% to about 0.10% carbon, about 0.1% to about 0.5% titanium, and the balance essentially copper which comprises heating the alloy at a temperature of about 1150 F. for about 2 to about 8 hours, furnace cooling to about 1050 F., holding at about 1050 F. for about 2 to about 6 hours, furnace cooling to about 950 F., and holding at about 950 F. for about 2 to about 6 hours.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)
  • Conductive Materials (AREA)
  • Forging (AREA)
US715898A 1968-03-25 1968-03-25 Nickel-copper alloy Expired - Lifetime US3578440A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US71589868A 1968-03-25 1968-03-25

Publications (1)

Publication Number Publication Date
US3578440A true US3578440A (en) 1971-05-11

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US715898A Expired - Lifetime US3578440A (en) 1968-03-25 1968-03-25 Nickel-copper alloy

Country Status (6)

Country Link
US (1) US3578440A (de)
BE (1) BE730405A (de)
DE (1) DE1914632A1 (de)
FR (1) FR2004669A1 (de)
GB (1) GB1225721A (de)
SE (1) SE342473B (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4642495A (en) * 1982-02-19 1987-02-10 Hitachi, Ltd. Electric rotary machine having superconducting rotor
US4729799A (en) * 1986-06-30 1988-03-08 United Technologies Corporation Stress relief of single crystal superalloy articles
US5980653A (en) * 1997-01-23 1999-11-09 Ngk Metals Corporation Nickel-copper-beryllium alloy compositions
RU2600787C1 (ru) * 2015-06-25 2016-10-27 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Медно-никелевый сплав и изделие, выполненное из него

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107653399A (zh) * 2017-09-22 2018-02-02 太仓捷公精密金属材料有限公司 一种耐腐蚀铜镍合金
CN112195370B (zh) * 2020-09-23 2022-01-25 北京通嘉鼎元科技有限公司 高镍合金材料及其制备方法和铸铁件

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4642495A (en) * 1982-02-19 1987-02-10 Hitachi, Ltd. Electric rotary machine having superconducting rotor
USRE33186E (en) * 1982-02-19 1990-03-27 Hitachi, Ltd. Electric rotary machine having superconducting rotor
US4729799A (en) * 1986-06-30 1988-03-08 United Technologies Corporation Stress relief of single crystal superalloy articles
US5980653A (en) * 1997-01-23 1999-11-09 Ngk Metals Corporation Nickel-copper-beryllium alloy compositions
US6093264A (en) * 1997-01-23 2000-07-25 Ngk Metals Corporation Nickel-copper-beryllium alloy compositions
RU2600787C1 (ru) * 2015-06-25 2016-10-27 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Медно-никелевый сплав и изделие, выполненное из него

Also Published As

Publication number Publication date
FR2004669A1 (de) 1969-11-28
GB1225721A (de) 1971-03-24
BE730405A (de) 1969-09-25
DE1914632A1 (de) 1969-10-09
SE342473B (de) 1972-02-07

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