[go: up one dir, main page]

US3164465A - Nickel-base alloys - Google Patents

Nickel-base alloys Download PDF

Info

Publication number
US3164465A
US3164465A US236390A US23639062A US3164465A US 3164465 A US3164465 A US 3164465A US 236390 A US236390 A US 236390A US 23639062 A US23639062 A US 23639062A US 3164465 A US3164465 A US 3164465A
Authority
US
United States
Prior art keywords
percent
nickel
titanium
aluminum
elongation
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US236390A
Inventor
Rudolf H Thielemann
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.)
MARTIN METALS CO
Original Assignee
MARTIN METALS CO
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MARTIN METALS CO filed Critical MARTIN METALS CO
Priority to US236390A priority Critical patent/US3164465A/en
Application granted granted Critical
Publication of US3164465A publication Critical patent/US3164465A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%

Definitions

  • This invention relates to nonferrous alloys. More particularly, it relates to nickel-base casting alloys having improved strength. Still more particularly, it relates to nickel-base alloys which include alloying metal additives capable of imparting to the resultant alloys corrosion resistance and great mechanical work strength at temperatures up to about 2000 F.
  • alloys are prepared which can be cast into forms useful for high stress applications and under oxidizing conditions, comprising a chromium-containing nickel-base alloy having tungsten, columbium, titanium, and aluminum present in proportions and in a relationship one to the other necessary to attain the properties at high temperatures of rupture strength, resistance to oxidation, high impact and high fatigue strength, resistance to grain boundary deformation and intergranular cracking.
  • One form of prior art commercially available nickelbase casting alloy is indicated to have a life of 100 hours at temperatures of about 1800 F. and at loads of about 15,000 p.s.i. This alloy falls off rapidly in rupture life if either the stress is increased while maintaining a temperature of 1800 F. or if the temperature is increased appreciable above this 1800 F. level. Data presented by the inventors of this alloy shows that one containing 4.05% of titanium and critical amounts of cobalt, chromium, boron, and zirconium at 1800 F. and 25,000 p.s.i. has a rupture life of only 17.2 hours.
  • Blades for gas turbine engines cast from alloys of this type containing amounts of titanium in the range of about 3.5% to 5% appear to be sensitive to cracking and have up to the present time not been accepted for use under the highly stressed, high temperature (about 1800" F.) conditions under which they are designed to operate.
  • This operating temperature is currently being specified by designers because performance of gas turbine engines operating at such higher temperature is improved, in that with this higher temperature the total thrust of the engine is increased.
  • the metal alloy of this invention is comprised by Weight of: from about 6% to about 17% of chromium; from about 5% to about 20% of tungsten; from about 0.25% to about 3% of columbium or tantalum or mixtures thereof; from about 2% to about 8% of aluminum; from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum; from about 2% to about of cobalt; at least one of the metals in the amounts indicated selected from the group consisting of from about 0.001% to about 0.5 of zirconium and from about 0.001% to about 0.2% of boron; from about 0.02% to about 0.35% of carbon; and the remainder being nickel and incidental impurities, the nickel content being in the range of about 45% to about 77%.
  • the alloys of this invention consist essentially of a nickel-base solid solution matrix containing tungsten to attain thermal stability and a relatively high melting point.
  • a nickel-tungsten system containing up to tungsten tolerates substantial alloying with other metals without becoming embrittled.
  • Aluminum and chromium are added to this basic composition for the purposes of improving oxidation resistance.
  • Aluminum serves a dual purpose. In addition to imparting oxidation resistance, it functions to form an intermetallic compound with nickel, which is an excellent hardener and strengthener of the alloy.
  • Chromium serves primarily to impart oxidation resistance. Too large quantities of chromium detracts from the strength of the alloy. Chromium in quantities of about 17% is optimum for oxidation resistance, but above 15%, the deleterious effect of chromium on strength tends to become apparent and above 17% the reduction in strength becomes objectionable.
  • chromium is used in quantities in the range between about 8% and about 12%.
  • Titanium is an important element in determining the strength of the alloys of this invention, both at room temperature and at elevated temperatures. Small amounts of titanium are useful in the alloy because of a strengthening effect on the matrix. Quantities above about 3% are deleterious because alloys of the higher titanium content show a tendency to cracking.
  • titanium is used in quantities in the range between about 0.75% and about 2.5%. Inasmuch as the alloys contain titanium and aluminum, a balance must be maintained whereby formation of an intermetallic compound Ni (AlTi) is favored. In order to accomplish this re sult, it is preferable that the aluminum to titanium weight ratio be in the range between about 2:1 and about 6:1.
  • columbium and tantalum can be used interchangeably. Columbium and tantalum serve to stabilize the carbon which is present in the matrix, and to be effective should be present in amounts between about 7 and about 10 times the weight percent of carbon, when operating under conditions of casting designed to give rapid solidification and uniform grain ize.
  • Carbon is required in this alloy in quantities to produce stable carbide hardeners.
  • the strength and the ductility of the alloy is highest when the carbon content is above about 0.1% and in proportions to combine with the columbium or tantalum due to its preferential afiinity therefor, thereby leaving the titanium to form predominantly an intermetallic hardening compound with nickel.
  • the high temperature metallurgical stability and strength characteristics of the alloys of this invention are improved by the addition to the alloys of boron and/ or zirconium in the respective specified amounts.
  • Molybdenum is an optional element in this alloy and may only be present without deleteriously affecting the properties of the. alloy if the amount thereof does not eX- ceed 3% by weight of the alloy.
  • interstitial and impurity elements such as nitrogen, hydrogen, tin, lead, and the like, should be kept as low in concentration in the alloys as possible.
  • deoxodizers such as calcium, magnesium, and the like, should be present.
  • a preferred range of proportions of constituents of the alloy of this invention in percentages byweight is as follows: from about 8.75% to about 10.25% of chromium; from about 11% to about 16% of tungsten; from about 0.8% to about 1.8% of columbium or tantalum or'mixtures thereof; from' about 4.75% to about 5.5% of aluminum; from about 0.75% to about 2.5% of titanium with the provision that the titanium does not exceed the amount of aluminum; from about 8% to about 12% of cobalt; at least one metal in the amounts indicated selected from the elements consisting of from about 0.03% to about 0.12% of zirconium and from about 0.01% to about 0.03% of boron; from about 0.12% to about 0.17% of carbon; about 1.5% maximum of iron; about 0.10% maximum of silicon; about 0.10% maximum of manganese and the remainder being nickel and incidental impurities, the nickel content being in the range of about 50% to about 77%.
  • Example I A pound alloy melt of a nickel-base metal alloy composition containing 6 percent of chromium, 15 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of boron, 0.15 percent of carbon, percent of cobalt, and the balance essentially nickel, all by weight, was prepared by melting a chromium-nickel mix in a magnesia crucible under high vacuum conditions, following which the tungsten, columbium, aluminum, titanium, boron, cobalt and carbon were added, the latter in the form of graphite.
  • the composition had an equivalency value of 62.8.
  • a cluster of 6.test bars was formed from the 5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars were each 3 inches long and 4 inch in diameter.
  • test bars had at rupture an elongation of about 3.5 percent and a tensile strength of 150,000 p.s.i.
  • test bars had anelongation of 2 percent with a rupture life in excess of 400 hours under a load of 17,- 000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 6 percent with a rupture life in excess of 300 hours under a load of 20,000 p.s.i. at a temperature of 1800 F. in air.
  • the test bars had an elongation of about 3 percent with a rupture life in excess of. 150 hours under a load of 12,500 p.s.i. at a temperature of 1900 F. in air, and an elongation of 5 percent with a rupture life in excess of 100 hours under a load of 15,000 p.s.i. at a temperature of 1900 F. in air.
  • Example II A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 7 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 6 percent of aluminum, 1 percent of titanium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I.
  • the composition had an equivalency value of 64.5.
  • test bars had at rupture an elongation of 3.3 percent and a tensile strength of 127,- 000 p.s.i.
  • test bars had an elongation of 4.1v percent with a rupture life in excess of 460 hours under a load of 17,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 2.5 percent with a rupture life in excess of hours under a load of 12,500 p.s.i. at a temperature of about 1900 F. in air.
  • Example 111 A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1' percent of columbium, 5.0 percent of aluminum, 2 percent of titanium, 0.05 percent of zirconium, 0.015 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 64.75.
  • test bars had at rupture an elongation of 4.0 percent and a tensile strength of 139,000 p.s.i.
  • test bars had an elongation of 7.5 percent with a rupture life of 86.8 hours under a load of 29,000 p.s.i.
  • Example IV A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 7 percent of chromium, 12 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 3 percent of molyb denum, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 60.5.
  • test .bars had at rupture an elongation of 2.7 percent and a tensile strength of 150,000 p.s.i.
  • test bars had an elongation of 1.9 percent with a rupture life in excess of 350 hours under a load of 17,000 p.s.i. at a temperature of 1800 F. in air.
  • Example V A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 7 percent of chromium, 20 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I.
  • the composition had an equivalency value of 69.3.
  • test bars had at rupture an elongation of 2.0 percent and a tensile strength of 150,000 p.s.i.
  • test bars had an elongation of 1.3 percent with a rupture life in excess of 350 hours under a load of 17,000 p.s.i. at a temperature of1800 F. in air.
  • Example VI manner as set forth in Example I.
  • the composition had an equivalency value of 66.25.
  • test bars had at rupture an elongation of 4.1 percent and a tensile strength of 149,000 p.s.i.
  • the test bars had an elongation of 7.5 percent with a rupture life of 398 hours under a load of 20,000 p.s.i. and an elongation of 3.3 percent with a rupture life of 160 hours under a load of 25,000 p.s.i., all at a temperature of 1800 F.
  • the test bars had an elongation of 4.1 percent with a rupture life in excess of 192 hours under a load of 15,000 p.s.i. and an elongation of 2.5 percent with a rupture life in excess of 99 hours under a load of 17,500 p.s.i., all at a temperature of 1900 F.
  • Example VII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 6 percent of aluminum, 1 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, Were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 66.7.
  • test bars had at rupture an elongation of 3.3 percent and a tensile strength of 157,000 p.s.i.
  • the test bars had an elongation of 1.6 percent with a rupture life in excess of 195 hours under a load of 20,000 p.s.i., and an elongation of 1.6 percent with a rupture life in excess of 140 hours under a load of 25,000 p.s.i., all at a temperature of 1800 F.
  • the test bars had an elongation of 5 percent with a rupture life in excess of 350 hours under a load of 15,000 p.s.i. and an elongation of 2.5 percent with a rupture life in excess of 119 hours under a load of 17,500 p.s.i., all at a temperature of 1900 F.
  • Example VIII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 16 percent of chromium, 8 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 65.1.
  • test bars had at rupture an elongation of 0.8 percent and a tensile strength of 147,100 p.s.i.
  • test bars had an elongation of 6.6 percent with a rupture life in excess of 180 hours under ,aload of 17,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 11.6 percent with a rupture life in excess of 40 hours under a load of 12,500.p.s.i. at a temperature of 1900 F. in air.
  • Example IX A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 1-6 percent. of chromium, 18 percent of tungsten, 1 percent of columbium, 2.0 percent of aluminum, 2.0 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 59.8.
  • test bars had at rupture an elongation of 2.1 percent and a tensile strength of 150,000 p.s.i.
  • test bars had an elongation of 7.6 percent with a rupture life in excess of 240 hours under a load of 17,000 p.s.i. at a temperature of 1800 F. in air.
  • Example X A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 15 percent of chromium, 10 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 66.4.
  • test bars had at rupture an elongation of 0.8 percent and a tensile strength of 157,800 p.s.1.
  • test bars had an elongation of 5 percent with a rupture life in excess of 180 hours under a load of 20,000 p.s.i., and an elongation of 3.3 percent with a rupture life in excess of 63 hours under. a load of 25,000 p.s.i., all at a temperature of 1800 F.
  • the test bars had an elongation of 6.6 percent with a rupture life in excess of 36 hours under a load of 17,500 p.s.i. at a temperature of 1900 F.
  • Example XI A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 15 percent of tungsten, 1.25 percent of columbium, 5.25 percent of aluminum, 1 percent of titanium, 0.08 percent of zirconium, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 65.55.
  • test bars had at rupture an elongation of 2.5 percent and a tensile strength of 140,000
  • test bars had an elongation of 8.0 percent with a rupture life in excess of 34.1 hours under a load of 27,500 p.s.i. at a temperature of 1800 F. in air.
  • Example XII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 15 percent of tungsten, 2 percent of tantalum, 5.25 percent of aluminum, 1 percent of titanium, 0.08 percent of zirconiurh, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 68.1.
  • test bars had at rupture an elongation of 2.5 percent and a tensile strength of 155,000 p.s.1.
  • test bars had an elongation of 8.0 percent with a rupture life of 46 hours under a load of 27,500 p.s.i. at a temperature of 1800 F. in air.
  • the test bars had an elongation of 10 percent with a rupture life in excess of 17.8 hours under a load of 20,000 p.s.i. at a temperature of 1900 F. in air.
  • Example XIII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 5 .25 percent of aluminum, 0 percent of titanium, 0.02 percent of boron, 0.08 percent of zirconium, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 57.65. i
  • test bars had at rupture an elongation of 1.5 percent and a tensile strength of 121,200 p.s.1.
  • test bars had an elongation of 4.6 percent with a rupture life of 75.7 hours under a load of 20,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 5.3 percent with a rupture life of 12.3 hours under a load of 17,500 p.s.i. at a temperature of 1900 F.
  • the test bars had an elongation of 13 percent with a rupture life of 0.9 hour under a load of 15,000 p.s.i.
  • Example XIV A pound alloy melt of nickel-base metal alloy composition containing 9 percent chromium, 12.5 percent tungsten, 1 percent columbium, 5.25 percent aluminum, 0.5 percent titanium, 0.08 percent zirconium, 0.02 percentboron, 0.15 percent carbon, percent cobalt, and the balance essentially nickel, all by weight, was prepared by melting a chromium-nickel mix in. a magnesia crucible under high vacuum conditions, following which the tungsten, columbium, aluminum, titanium, boron, cobalt and carbon were added, the latter in the form of graphite. The composition had an equivalency value of 59.9.
  • test bars were formed from the 5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars Were each 3 inches long and /4 inch in diameter.
  • test bars had at rupture an elongation of 3.0 percent and a tensile strength of 151,000
  • test bars had an elongation of 4.6 percent with a rupture life of 397.9 hours under a load of 20,000 p.s.i. at a temperature or" 1800 F. in air, and an elongation of 9.2 percent with a rupture life of 54 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. in air.
  • the test bars had an elongation of about 10 percent with a rupture life in excess of 4.2 hours under a load'of 15,000 p.s.i. at a temperature of 2000 F. in air.
  • Example XV A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-basemetal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 5.25 percent of aluminum, 2 percent of titanium, 0.08 percent zirconium, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner .as set forth in Example I. The composition had 'an equivalency valueof 66.25.
  • test bars had at rupture an elongation 'of 2.3 percent and a tensile strength of 139,500 p.s.i.
  • the test bars had an elongation of 4.6 percent with a rupture life of 1,045 hours under a load of 20,00'0p.s.i. at a temperature of 1 800 F. in air, and an elongation of 4.5% with a rupture life of 58.8 hours under a load of 29,000 p.s.i. at a temperature of 1800 F., and an elongation of 3 percent with a rupture life of 147 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. in air.
  • the test bars had an elongation of 3 percent with a rupture life of 19.3 hours under a load of 15,000 p.s.i. at a temperature of 2000 F.
  • Example XVI A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 5.25 percent of aluminum, 2.5 percent of titanium, 0.08 percent zirconium, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set 3 forth in Example I. The composition had an equivalency value of 68.4.
  • test bars had at rupture an elongation of 2.3 percent and a tensile strength of 140,500 p.s.i.
  • the test bars had an elongation of 3 percent with a rupture life of 656.8 hours under a load of 20,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 2.3 percent with a rupturelife of 173.2 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. in air.
  • the test bars had an elongation of 2.3 percent mm a rupture life in excess of 20.3 hours under a load of 15,000 p.s.i. at a temperature of 2000 F.
  • test bars were formed from the '5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars were each 3 inches long and A inch in diameter.
  • test bars had at rupture an elongation of 3.8 percent and a tensile strength of 141,600 p.s.i.
  • Example XVIII A 5 pound alloy melt of nickel-base metal alloy composition containing 10 percent chromium, 15 percent tungsten, 1.5 percent tantalum, 5.0 percent aluminum, 1.0
  • the composition had an equivalency value of A cluster of 6 test bars were formed from the 5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars were each 3 inches long and inch in diameter.
  • test bars had at rupture an elongation of 3.0 percent and a tensile strength of 135,000 p.s.1.
  • test bars had an elongation of 5.0 percent with a rupture life of 200 hours under a load of 25,000 p.s.i. at a temperature of 1800 F. in air.
  • Examples I, V, VIII, and IX shows the adverse effect of high chromium content and the counterbalancing effect possible through changes in composition provided the equivalency factor does not exceed 70.
  • Example 4 shows that up to 3 percent molybdenum can be tolerated without appreciable deleterious effect.
  • Examples XIII to XVII inclusive show the eifect of changes in titanium content in otherwise identical compositions and the reduction in rupture life when the titanium is increased to 3.5 percent and higher. This reduction in rupture lifeis in addition to other deficiencies such as cracking, brittle mode of fracture and decreased oxidation resistance.
  • a metal alloy consisting essentially of, by weight, from about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25 to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum, from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 2% to about 15% of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.001% to about 0.5% of zirconium land from about 0.001% to about 0.2% of boron, from about 0.02% to about 0.35% of carbon, and the remainder being nickel and incidental impurities, said nickel content being in the range of about 45% to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
  • a metal alloy consisting essentially of, by weight, from about 8.75% to about 10.25% of chromium, from about 11% to about 16% of tungsten, from about 0.8% to about 1.8% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 4.75% to about 5.5% of aluminum, from about 0.75% to about 2.5% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 8% to about 12% of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.03% to about 0.12% of zirconium and from about 0.01% to about 0.03 of boron, from about 0.12% to about 0.17 of carbon, and the remainder being nickel and incidental impurities, said nickel content being in the range of about 50% to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting
  • a metal alloy consisting essentially of, by weight, rom about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25% to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum, from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 2% to about 15 of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.001% to about 0.5% of zirconium and from about 0.001% to about 0.2% of boron, from about 0.02% to about 0.35% of carbon, from about to about of iron, from about 0% to about 1% of silicon, from about 0% to about 2% of manganese, from about 0% to about 3% of molybdenum, the remainder being nickel and incident
  • a metal alloy consisting essentially of, by weight, from about 8.75% to about 10.25% of chromium, from about 11% to about 16% of tungsten, from about 0.8% to about 1.8% of at least one of the metals selected from the group consisitng of columbium and tantalum, from about 4.75% to about 5.5% of aluminum, from about 0.75% to about 2.5% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 8% to about 12% of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.03% to about 0.12% of zirconium and from about 0.01% to about 0.03% of boron, from about 0.12% to about 0.17% of carbon, from about 0% to about 5% of iron, from about 0% to about 1% of silicon, from about 0% to about 2% of manganese, from about 0% to about 3% of moly
  • a metal alloy consisting essentially of, by weight, from about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25% to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum.
  • a metal alloy consisting esesntially of, by weight, from about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25% to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum,from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 2% to about 15 of cobalt, from about 0.001% to about 0.5% of zirconium, from about 0.02% to about 0.35 of carbon, the remainder being nickel and incidental impurities, said nickel content bieng in the range of about 45 to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
  • a metal alloy consisting essentially of, by weight, from about 8.75 to about 10.25 of chromium, from about 11% to about 16% of tungsten, from about 0.8% to about 1.8% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 4.75% to about 5.5 of aluminum, from about 0.75% to about 2.5% of titanium with the provision that the titanium does not exceed the amount of aluminum, from about 8% to about 12% of cobalt, from about 0.01% to about 0.03% of boron, from about 0.12% to about 0.17% of carbon, the remainder being nickel and incidental impurities, said nickel content being in the range of about 50% to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
  • a metal alloy consisting essentially of, by approximate weight, 9% of chromium, 12.5% of tungsten, 1% of columbium, 0.05% of zirconium, 0.015% of boron, 2% of titanium, 0.15% of carbon, 5.0% of aluminum, 10% of cobalt, and the balance essentially nickel.
  • a metal alloy consisting essentially of, by approximate weight, 10% of chromium, 15% of tungsten, 1.5% of tantalum, 0.05% of zirconium, 0.015% of boron, 1%

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

United States Patent 3,164,465 NICKEL-BASE ALLOYS Rudolf H. Thielemann, Portland, Oreg., assignor to Martin Metals Company, a corporation of Delaware No Drawing. Filed Nov. 8, 1962, Ser. No. 236,390 9 Claims. (Cl. 75-171) This invention relates to nonferrous alloys. More particularly, it relates to nickel-base casting alloys having improved strength. Still more particularly, it relates to nickel-base alloys which include alloying metal additives capable of imparting to the resultant alloys corrosion resistance and great mechanical work strength at temperatures up to about 2000 F.
This application is a continuation-in-part of my application Serial No. 791,276, filed February 5, 1959, now abandoned, and entitled Metal Alloy.
In accordance with the present invention, alloys are prepared which can be cast into forms useful for high stress applications and under oxidizing conditions, comprising a chromium-containing nickel-base alloy having tungsten, columbium, titanium, and aluminum present in proportions and in a relationship one to the other necessary to attain the properties at high temperatures of rupture strength, resistance to oxidation, high impact and high fatigue strength, resistance to grain boundary deformation and intergranular cracking.
One form of prior art commercially available nickelbase casting alloy is indicated to have a life of 100 hours at temperatures of about 1800 F. and at loads of about 15,000 p.s.i. This alloy falls off rapidly in rupture life if either the stress is increased while maintaining a temperature of 1800 F. or if the temperature is increased appreciable above this 1800 F. level. Data presented by the inventors of this alloy shows that one containing 4.05% of titanium and critical amounts of cobalt, chromium, boron, and zirconium at 1800 F. and 25,000 p.s.i. has a rupture life of only 17.2 hours. Blades for gas turbine engines cast from alloys of this type containing amounts of titanium in the range of about 3.5% to 5%, appear to be sensitive to cracking and have up to the present time not been accepted for use under the highly stressed, high temperature (about 1800" F.) conditions under which they are designed to operate. This operating temperature is currently being specified by designers because performance of gas turbine engines operating at such higher temperature is improved, in that with this higher temperature the total thrust of the engine is increased.
Basically, the metal alloy of this invention is comprised by Weight of: from about 6% to about 17% of chromium; from about 5% to about 20% of tungsten; from about 0.25% to about 3% of columbium or tantalum or mixtures thereof; from about 2% to about 8% of aluminum; from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum; from about 2% to about of cobalt; at least one of the metals in the amounts indicated selected from the group consisting of from about 0.001% to about 0.5 of zirconium and from about 0.001% to about 0.2% of boron; from about 0.02% to about 0.35% of carbon; and the remainder being nickel and incidental impurities, the nickel content being in the range of about 45% to about 77%.
The alloys of this invention consist essentially of a nickel-base solid solution matrix containing tungsten to attain thermal stability and a relatively high melting point. A nickel-tungsten system containing up to tungsten tolerates substantial alloying with other metals without becoming embrittled.
Aluminum and chromium are added to this basic composition for the purposes of improving oxidation resistance. Aluminum serves a dual purpose. In addition to imparting oxidation resistance, it functions to form an intermetallic compound with nickel, which is an excellent hardener and strengthener of the alloy. Chromium serves primarily to impart oxidation resistance. Too large quantities of chromium detracts from the strength of the alloy. Chromium in quantities of about 17% is optimum for oxidation resistance, but above 15%, the deleterious effect of chromium on strength tends to become apparent and above 17% the reduction in strength becomes objectionable. Preferably, chromium is used in quantities in the range between about 8% and about 12%. Titanium is an important element in determining the strength of the alloys of this invention, both at room temperature and at elevated temperatures. Small amounts of titanium are useful in the alloy because of a strengthening effect on the matrix. Quantities above about 3% are deleterious because alloys of the higher titanium content show a tendency to cracking. Preferably, titanium is used in quantities in the range between about 0.75% and about 2.5%. Inasmuch as the alloys contain titanium and aluminum, a balance must be maintained whereby formation of an intermetallic compound Ni (AlTi) is favored. In order to accomplish this re sult, it is preferable that the aluminum to titanium weight ratio be in the range between about 2:1 and about 6:1. In the alloys of this invention, columbium and tantalum can be used interchangeably. Columbium and tantalum serve to stabilize the carbon which is present in the matrix, and to be effective should be present in amounts between about 7 and about 10 times the weight percent of carbon, when operating under conditions of casting designed to give rapid solidification and uniform grain ize.
Carbon is required in this alloy in quantities to produce stable carbide hardeners. The strength and the ductility of the alloy is highest when the carbon content is above about 0.1% and in proportions to combine with the columbium or tantalum due to its preferential afiinity therefor, thereby leaving the titanium to form predominantly an intermetallic hardening compound with nickel.
The high temperature metallurgical stability and strength characteristics of the alloys of this invention are improved by the addition to the alloys of boron and/ or zirconium in the respective specified amounts. In many instances it is preferred to maintain the Weight ratio of zirconium to boron in the alloy at about 4:1, although other weight ratios have also been found stable. It has been found that if the boron content of the alloy exceeds 0.2%, then the alloy may be unsatisfactory, particularly in those applications where thermal shock requirements are important.
Molybdenum is an optional element in this alloy and may only be present without deleteriously affecting the properties of the. alloy if the amount thereof does not eX- ceed 3% by weight of the alloy.
While silicon, manganese, and iron are not essential ingredients of the alloys of the present invention, it has been found that the addition of small percentages of any one or more of these ingredients, that is, up to about 1% of silicon, up to about 2% of manganese, and up to about 5% of iron, may in'certain instances somewhat improve certain properties of the alloy.
The interstitial and impurity elements, such as nitrogen, hydrogen, tin, lead, and the like, should be kept as low in concentration in the alloys as possible. In addition, no more than about 0.5% total of the deoxodizers, such as calcium, magnesium, and the like, should be present.
A preferred range of proportions of constituents of the alloy of this invention in percentages byweight is as follows: from about 8.75% to about 10.25% of chromium; from about 11% to about 16% of tungsten; from about 0.8% to about 1.8% of columbium or tantalum or'mixtures thereof; from' about 4.75% to about 5.5% of aluminum; from about 0.75% to about 2.5% of titanium with the provision that the titanium does not exceed the amount of aluminum; from about 8% to about 12% of cobalt; at least one metal in the amounts indicated selected from the elements consisting of from about 0.03% to about 0.12% of zirconium and from about 0.01% to about 0.03% of boron; from about 0.12% to about 0.17% of carbon; about 1.5% maximum of iron; about 0.10% maximum of silicon; about 0.10% maximum of manganese and the remainder being nickel and incidental impurities, the nickel content being in the range of about 50% to about 77%.
In preparing the alloys of this invention, it has been found that a balance is required between the amounts of chromium, tungsten, columbium or tantalum, tita nium and aluminum present in the alloy if the desired high temperature characteristics are to be developed. Particularly when varying the amounts of the specified components within the specified ranges, the improved oxidation and strength properties characterizing the alloys will be maintained if the alloy formulations are prepared in accordance with the foregoing, and, furthermore, in accordance with the following equation:
with the percentages by weight of the respective constituents of the alloy substituted into the equation.
Following are examples of the preparation and test results of various formulations of the nickel-base metal alloy of this invention, in the approximate weight percentages indicated.
Example I A pound alloy melt of a nickel-base metal alloy composition containing 6 percent of chromium, 15 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of boron, 0.15 percent of carbon, percent of cobalt, and the balance essentially nickel, all by weight, was prepared by melting a chromium-nickel mix in a magnesia crucible under high vacuum conditions, following which the tungsten, columbium, aluminum, titanium, boron, cobalt and carbon were added, the latter in the form of graphite. The composition had an equivalency value of 62.8.
A cluster of 6.test bars was formed from the 5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars were each 3 inches long and 4 inch in diameter.
At room temperature the test bars had at rupture an elongation of about 3.5 percent and a tensile strength of 150,000 p.s.i.
The test bars had anelongation of 2 percent with a rupture life in excess of 400 hours under a load of 17,- 000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 6 percent with a rupture life in excess of 300 hours under a load of 20,000 p.s.i. at a temperature of 1800 F. in air. The test bars had an elongation of about 3 percent with a rupture life in excess of. 150 hours under a load of 12,500 p.s.i. at a temperature of 1900 F. in air, and an elongation of 5 percent with a rupture life in excess of 100 hours under a load of 15,000 p.s.i. at a temperature of 1900 F. in air. 3
Example II *A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 7 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 6 percent of aluminum, 1 percent of titanium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 64.5.
At room temperature the test bars had at rupture an elongation of 3.3 percent and a tensile strength of 127,- 000 p.s.i.
The test bars had an elongation of 4.1v percent with a rupture life in excess of 460 hours under a load of 17,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 2.5 percent with a rupture life in excess of hours under a load of 12,500 p.s.i. at a temperature of about 1900 F. in air.
Example 111 A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1' percent of columbium, 5.0 percent of aluminum, 2 percent of titanium, 0.05 percent of zirconium, 0.015 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 64.75.
At room temperature the test bars had at rupture an elongation of 4.0 percent and a tensile strength of 139,000 p.s.i.
The test bars had an elongation of 7.5 percent with a rupture life of 86.8 hours under a load of 29,000 p.s.i.
' at a temperature of 1800 F. in air.
Example IV A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 7 percent of chromium, 12 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 3 percent of molyb denum, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 60.5.
At room temperature the test .bars had at rupture an elongation of 2.7 percent and a tensile strength of 150,000 p.s.i.
The test bars had an elongation of 1.9 percent with a rupture life in excess of 350 hours under a load of 17,000 p.s.i. at a temperature of 1800 F. in air.
Example V A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 7 percent of chromium, 20 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 69.3.
At room temperature the test bars had at rupture an elongation of 2.0 percent and a tensile strength of 150,000 p.s.i.
The test bars had an elongation of 1.3 percent with a rupture life in excess of 350 hours under a load of 17,000 p.s.i. at a temperature of1800 F. in air.
. Example VI manner as set forth in Example I. The composition had an equivalency value of 66.25.
At room temperature the test bars had at rupture an elongation of 4.1 percent and a tensile strength of 149,000 p.s.i.
The test bars had an elongation of 7.5 percent with a rupture life of 398 hours under a load of 20,000 p.s.i. and an elongation of 3.3 percent with a rupture life of 160 hours under a load of 25,000 p.s.i., all at a temperature of 1800 F. The test bars had an elongation of 4.1 percent with a rupture life in excess of 192 hours under a load of 15,000 p.s.i. and an elongation of 2.5 percent with a rupture life in excess of 99 hours under a load of 17,500 p.s.i., all at a temperature of 1900 F.
Example VII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 6 percent of aluminum, 1 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, Were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 66.7.
At room temperature the test bars had at rupture an elongation of 3.3 percent and a tensile strength of 157,000 p.s.i.
The test bars had an elongation of 1.6 percent with a rupture life in excess of 195 hours under a load of 20,000 p.s.i., and an elongation of 1.6 percent with a rupture life in excess of 140 hours under a load of 25,000 p.s.i., all at a temperature of 1800 F. The test bars had an elongation of 5 percent with a rupture life in excess of 350 hours under a load of 15,000 p.s.i. and an elongation of 2.5 percent with a rupture life in excess of 119 hours under a load of 17,500 p.s.i., all at a temperature of 1900 F.
Example VIII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 16 percent of chromium, 8 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 65.1.
At room temperature the test bars had at rupture an elongation of 0.8 percent and a tensile strength of 147,100 p.s.i.
The test bars had an elongation of 6.6 percent with a rupture life in excess of 180 hours under ,aload of 17,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 11.6 percent with a rupture life in excess of 40 hours under a load of 12,500.p.s.i. at a temperature of 1900 F. in air.
Example IX A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 1-6 percent. of chromium, 18 percent of tungsten, 1 percent of columbium, 2.0 percent of aluminum, 2.0 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 59.8.
At room temperature the test bars had at rupture an elongation of 2.1 percent and a tensile strength of 150,000 p.s.i.
The test bars had an elongation of 7.6 percent with a rupture life in excess of 240 hours under a load of 17,000 p.s.i. at a temperature of 1800 F. in air.
Example X A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 15 percent of chromium, 10 percent of tungsten, 1 percent of columbium, 4 percent of aluminum, 3 percent of titanium, 0.05 percent of zirconium, 0.05 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 66.4.
At room temperature the test bars had at rupture an elongation of 0.8 percent and a tensile strength of 157,800 p.s.1.
The test bars had an elongation of 5 percent with a rupture life in excess of 180 hours under a load of 20,000 p.s.i., and an elongation of 3.3 percent with a rupture life in excess of 63 hours under. a load of 25,000 p.s.i., all at a temperature of 1800 F. The test bars had an elongation of 6.6 percent with a rupture life in excess of 36 hours under a load of 17,500 p.s.i. at a temperature of 1900 F.
Example XI A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 15 percent of tungsten, 1.25 percent of columbium, 5.25 percent of aluminum, 1 percent of titanium, 0.08 percent of zirconium, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 65.55.
At room temperature the test bars had at rupture an elongation of 2.5 percent and a tensile strength of 140,000
The test bars had an elongation of 8.0 percent with a rupture life in excess of 34.1 hours under a load of 27,500 p.s.i. at a temperature of 1800 F. in air.
Example XII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 15 percent of tungsten, 2 percent of tantalum, 5.25 percent of aluminum, 1 percent of titanium, 0.08 percent of zirconiurh, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 68.1.
At room temperature the test bars had at rupture an elongation of 2.5 percent and a tensile strength of 155,000 p.s.1.
The test bars had an elongation of 8.0 percent with a rupture life of 46 hours under a load of 27,500 p.s.i. at a temperature of 1800 F. in air. The test bars had an elongation of 10 percent with a rupture life in excess of 17.8 hours under a load of 20,000 p.s.i. at a temperature of 1900 F. in air.
Example XIII A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 5 .25 percent of aluminum, 0 percent of titanium, 0.02 percent of boron, 0.08 percent of zirconium, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set forth in Example I. The composition had an equivalency value of 57.65. i
' At room temperature the test bars had at rupture an elongation of 1.5 percent and a tensile strength of 121,200 p.s.1.
The test bars had an elongation of 4.6 percent with a rupture life of 75.7 hours under a load of 20,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 5.3 percent with a rupture life of 12.3 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. The test bars had an elongation of 13 percent with a rupture life of 0.9 hour under a load of 15,000 p.s.i. at a temperature Example XIV A pound alloy melt of nickel-base metal alloy composition containing 9 percent chromium, 12.5 percent tungsten, 1 percent columbium, 5.25 percent aluminum, 0.5 percent titanium, 0.08 percent zirconium, 0.02 percentboron, 0.15 percent carbon, percent cobalt, and the balance essentially nickel, all by weight, was prepared by melting a chromium-nickel mix in. a magnesia crucible under high vacuum conditions, following which the tungsten, columbium, aluminum, titanium, boron, cobalt and carbon were added, the latter in the form of graphite. The composition had an equivalency value of 59.9.
A cluster of 6 test bars were formed from the 5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars Were each 3 inches long and /4 inch in diameter.
At room temperature the test bars had at rupture an elongation of 3.0 percent and a tensile strength of 151,000
The test bars had an elongation of 4.6 percent with a rupture life of 397.9 hours under a load of 20,000 p.s.i. at a temperature or" 1800 F. in air, and an elongation of 9.2 percent with a rupture life of 54 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. in air. The test bars had an elongation of about 10 percent with a rupture life in excess of 4.2 hours under a load'of 15,000 p.s.i. at a temperature of 2000 F. in air.
Example XV A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-basemetal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 5.25 percent of aluminum, 2 percent of titanium, 0.08 percent zirconium, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner .as set forth in Example I. The composition had 'an equivalency valueof 66.25.
At room temperature the test bars had at rupture an elongation 'of 2.3 percent and a tensile strength of 139,500 p.s.i.
The test bars had an elongation of 4.6 percent with a rupture life of 1,045 hours under a load of 20,00'0p.s.i. at a temperature of 1 800 F. in air, and an elongation of 4.5% with a rupture life of 58.8 hours under a load of 29,000 p.s.i. at a temperature of 1800 F., and an elongation of 3 percent with a rupture life of 147 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. in air. The test bars had an elongation of 3 percent with a rupture life of 19.3 hours under a load of 15,000 p.s.i. at a temperature of 2000 F.
Example XVI A 5 pound alloy melt and test bars of the same dimensions as set forth in Example I of a nickel-base metal alloy composition containing 9 percent of chromium, 12.5 percent of tungsten, 1 percent of columbium, 5.25 percent of aluminum, 2.5 percent of titanium, 0.08 percent zirconium, 0.02 percent of boron, 0.15 percent of carbon, 10 percent of cobalt, and the balance essentially nickel, all by weight, were prepared in the same manner as set 3 forth in Example I. The composition had an equivalency value of 68.4.
At room temperature the test bars had at rupture an elongation of 2.3 percent and a tensile strength of 140,500 p.s.i.
The test bars had an elongation of 3 percent with a rupture life of 656.8 hours under a load of 20,000 p.s.i. at a temperature of 1800 F. in air, and an elongation of 2.3 percent with a rupturelife of 173.2 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. in air. The test bars had an elongation of 2.3 percent mm a rupture life in excess of 20.3 hours under a load of 15,000 p.s.i. at a temperature of 2000 F.
Example XVII A 5 pound alloy melt of nickel-base metal alloy composition containing 9 percent chromium, 12.5 percent tungsten, 1 percent columbiurn, 5.25 percent aluminum, 3.5 percent titanium, 0.08 percent zirconium, 0.02 percent boron, 0.15 percent carbon, 10 percent cobalt, and the balance essentially nickel, all by weight, was prepared by melting a chromium-nickel mix in a magnesia crucible under high vacuum conditions, following which the tungsten, columbium, aluminum, titanium, and zirconium, boron, cobalt and carbon were added, the latter in the form of graphite. The composition had an equivalency value of 72.7.
A cluster of 6 test bars were formed from the '5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars were each 3 inches long and A inch in diameter.
At room temperature the test bars had at rupture an elongation of 3.8 percent and a tensile strength of 141,600 p.s.i.
The test bars had an elongation of 6.2 percent with a rupture life of 142.8 hours under a load of 20,000 p.s.i. at a temperature of 1800" F. in air, and an elongation of 3 percent with a rupture life of 88.9 hours under a load of 17,500 p.s.i. at a temperature of 1900 F. in air. The test bars had an elongation of about .76 percent with a rupture life of 15.7 hours under a load of 15,000 p.s.i. at a temperature of 2000 F. in air.
Example XVIII A 5 pound alloy melt of nickel-base metal alloy composition containing 10 percent chromium, 15 percent tungsten, 1.5 percent tantalum, 5.0 percent aluminum, 1.0
percent titanium, 0.015 percent boron, 0.05 percent zirconium, 0.15 percent carbon, 10 percent cobalt, and the balance essentially nickel, all by weight, was prepared by melting a chromium-nickel mix in a magnesia crucible under high vacuum conditions, following which the tungsten, tantalum, aluminum, titanium, boron, zirconium, cobalt and carbon were added, the latter in the form of ggaphite. The composition had an equivalency value of A cluster of 6 test bars were formed from the 5 pound melted alloy heated by the usual investment casting technique under high vacuum conditions. These bars were each 3 inches long and inch in diameter.
At room temperature the test bars had at rupture an elongation of 3.0 percent and a tensile strength of 135,000 p.s.1.
The test bars had an elongation of 5.0 percent with a rupture life of 200 hours under a load of 25,000 p.s.i. at a temperature of 1800 F. in air.
Comparison of Examples I, V, VIII, and IX shows the adverse effect of high chromium content and the counterbalancing effect possible through changes in composition provided the equivalency factor does not exceed 70. Example 4 shows that up to 3 percent molybdenum can be tolerated without appreciable deleterious effect. Examples XIII to XVII inclusive show the eifect of changes in titanium content in otherwise identical compositions and the reduction in rupture life when the titanium is increased to 3.5 percent and higher. This reduction in rupture lifeis in addition to other deficiencies such as cracking, brittle mode of fracture and decreased oxidation resistance.
The above detailed description of this invention has been given for clearness of understanding only. No unnecessary lirnitations should be understood therefrom, as modifications will be obvious to those skilled in the art.
Iclaim:
1. A metal alloy consisting essentially of, by weight, from about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25 to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum, from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 2% to about 15% of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.001% to about 0.5% of zirconium land from about 0.001% to about 0.2% of boron, from about 0.02% to about 0.35% of carbon, and the remainder being nickel and incidental impurities, said nickel content being in the range of about 45% to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
1 Cr+1.l W+3.4Cb (Ta) +4.3 Ti+6 Al=6070 2. A metal alloy consisting essentially of, by weight, from about 8.75% to about 10.25% of chromium, from about 11% to about 16% of tungsten, from about 0.8% to about 1.8% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 4.75% to about 5.5% of aluminum, from about 0.75% to about 2.5% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 8% to about 12% of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.03% to about 0.12% of zirconium and from about 0.01% to about 0.03 of boron, from about 0.12% to about 0.17 of carbon, and the remainder being nickel and incidental impurities, said nickel content being in the range of about 50% to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
1 Cr+1.1 W+3.4 Cb (Ta) +4.3 Ti+6 Al=6070 3. A metal alloy consisting essentially of, by weight, rom about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25% to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum, from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 2% to about 15 of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.001% to about 0.5% of zirconium and from about 0.001% to about 0.2% of boron, from about 0.02% to about 0.35% of carbon, from about to about of iron, from about 0% to about 1% of silicon, from about 0% to about 2% of manganese, from about 0% to about 3% of molybdenum, the remainder being nickel and incidental impurities, said nickel content being in the range of about 45% to about 77%, and said chromium tungsten, titanium, aluminum and metals selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
1 Cr+1.1 W+3.4 Cb (Ta)+4.3 Ti+6 Al=6070 4. A metal alloy consisting essentially of, by weight, from about 8.75% to about 10.25% of chromium, from about 11% to about 16% of tungsten, from about 0.8% to about 1.8% of at least one of the metals selected from the group consisitng of columbium and tantalum, from about 4.75% to about 5.5% of aluminum, from about 0.75% to about 2.5% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 8% to about 12% of cobalt, at least one of the metals in the amounts indicated selected from the group consisting of from about 0.03% to about 0.12% of zirconium and from about 0.01% to about 0.03% of boron, from about 0.12% to about 0.17% of carbon, from about 0% to about 5% of iron, from about 0% to about 1% of silicon, from about 0% to about 2% of manganese, from about 0% to about 3% of molybdenum, the remainder being nickel and incidental impurities, said nickel content being in the range of about 50% to about 77%, and said chromium, tungsten, titanium, aluminum and metals selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
1 Cr+l.1 W+3.4 Cb (Ta) +4.3 Ti+6 Al=6070 5. A metal alloy consisting essentially of, by weight, from about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25% to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum. from about 0.1% to about 3% of titanium with the aluminum to titanium weight ratio in the alloy being between about 2:1 and 6:1, from about 2% to about 15% of cobalt; at least one of the metals in the amounts indicated selected from the group consisting of from about 0.001% to about 0.5 of zirconium and from about 0.001% to about 0.2% of boron, from about 0.02% to about 0.35 of carbon, the remainder being nickel and incidental impurities, said nickel content being in the range of about 45 to about 77%, and said chromium, tungsten, titanium, aluminum and metals selected from the group consisting of columbium and tantalum being present in said alloy in weight percentage corresponding to the following equation:
1 Cr+l.l W+3.4 Cb (Ta) +4.3 Ti+6 Al=6070 6. A metal alloy consisting esesntially of, by weight, from about 6% to about 17% of chromium, from about 5% to about 20% of tungsten, from about 0.25% to about 3% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 2% to about 8% of aluminum,from about 0.1% to about 3% of titanium with the provision that the amount of titanium does not exceed the amount of aluminum, from about 2% to about 15 of cobalt, from about 0.001% to about 0.5% of zirconium, from about 0.02% to about 0.35 of carbon, the remainder being nickel and incidental impurities, said nickel content bieng in the range of about 45 to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
1 Cr+1.1 \V+3.4 Cb (Ta) +4.3 Ti+6 Al=6070 7. A metal alloy consisting essentially of, by weight, from about 8.75 to about 10.25 of chromium, from about 11% to about 16% of tungsten, from about 0.8% to about 1.8% of at least one of the metals selected from the group consisting of columbium and tantalum, from about 4.75% to about 5.5 of aluminum, from about 0.75% to about 2.5% of titanium with the provision that the titanium does not exceed the amount of aluminum, from about 8% to about 12% of cobalt, from about 0.01% to about 0.03% of boron, from about 0.12% to about 0.17% of carbon, the remainder being nickel and incidental impurities, said nickel content being in the range of about 50% to about 77%, and said chromium, tungsten, titanium, aluminum and metal selected from the group consisting of columbium and tantalum being present in said alloy in weight percentages corresponding to the following equation:
1 Cr+1.1 W+3.4 Cb (Ta) +4.3 Ti+6 Al=6070 8. A metal alloy consisting essentially of, by approximate weight, 9% of chromium, 12.5% of tungsten, 1% of columbium, 0.05% of zirconium, 0.015% of boron, 2% of titanium, 0.15% of carbon, 5.0% of aluminum, 10% of cobalt, and the balance essentially nickel.
9. A metal alloy consisting essentially of, by approximate weight, 10% of chromium, 15% of tungsten, 1.5% of tantalum, 0.05% of zirconium, 0.015% of boron, 1%
7 of titanium, 0.15% of carbon, 5.0% of aluminum,
of cobalt, and the balance essentially nickel.
References Cited in the file of this patent UNITED STATES PATENTS 2,587,275 Bash Feb. 26,
2,920,956 Nisbet et a1 Jan. 12,
2,948,606 Thielmann Aug. 9,
2,951,757 Brown Sept. 9,
FOREIGN PATENTS 710,413 Great Britain June 9,
OTHER REFERENCES Metallic Creep, Sully, Interscience Publishers, New York, 1959, page 240.
Inc.,

Claims (1)

1. A METAL ALLOY CONSISTING ESSENTIALLY OF, BY WEIGHT, FROM ABOUT 6% TO ABOUT 17% OF CHROMIUM, FROM ABOUT 5% TO ABOUT 20% OF TUNGSTEN, FROM ABOUT 0.25% TO ABOUT 3% OF AT LEAST ONE OF THE METALS SELECTED FROM THE GROUP CONSISTING OF COLUMBIUM AND TANTALUM, FROM ABOUT 2% TO ABOUT 8% OF ALUMINUM, FROM ABOUT 0.1% TO ABOUT 3% OF TITANIUM WITH THE PROVISION THAT THE AMOUNT OF TITANIUM DOES NOT EXCEED THE AMOUNT OF ALUMINUM, FROM ABOUT 2% TO ABOUT 15% OF COBALT, AT LEAST ONE OF THE METALS IN THE AMOUNTS INDICATED SELECTED FROM THE GROUP CONSISTING OF FROM ABOUT 0.001% TO ABOUT 0.5% OF ZIRCONIUM AND FROM ABOUT 0.001% TO ABOUT 0.2% OF BORON, FROM ABOUT 0.02% TO ABOUT 0.35% OF CARBON, AND THE REMAINDER BEING NICKEL AND INCIDENTAL IMPURITIES, SAID NICKEL CONTENT BEING IN THE RANGE OF ABOUT 45% TO ABOUT 77%, AND SAID CHROMIUM, TUNGSTEN, TITANIUM, ALUMINUM AND METAL SELECTED FROM THE GROUP CONSISTING OF COLUMBIUM AND TANTALUM BEIANG APRESENT IN SAID ALLOY IN WEIGHT PERCENTAGES CORRESPONDING TO THE FOLLOWING EQUATION:
US236390A 1962-11-08 1962-11-08 Nickel-base alloys Expired - Lifetime US3164465A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US236390A US3164465A (en) 1962-11-08 1962-11-08 Nickel-base alloys

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US236390A US3164465A (en) 1962-11-08 1962-11-08 Nickel-base alloys

Publications (1)

Publication Number Publication Date
US3164465A true US3164465A (en) 1965-01-05

Family

ID=22889292

Family Applications (1)

Application Number Title Priority Date Filing Date
US236390A Expired - Lifetime US3164465A (en) 1962-11-08 1962-11-08 Nickel-base alloys

Country Status (1)

Country Link
US (1) US3164465A (en)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3322534A (en) * 1964-08-19 1967-05-30 Int Nickel Co High temperature nickel-chromium base alloys
US3403059A (en) * 1965-06-24 1968-09-24 Gen Electric Nickel base alloy
US3459545A (en) * 1967-02-20 1969-08-05 Int Nickel Co Cast nickel-base alloy
US3473922A (en) * 1967-07-21 1969-10-21 Carondelet Foundry Co Corrosion-resistant alloys
US3508917A (en) * 1966-08-15 1970-04-28 Int Nickel Co Alloy for gas reformer tubes
US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties
US3617261A (en) * 1968-02-08 1971-11-02 Cyclops Corp Specialty Steel D Wrought nickel base superalloys
US3619182A (en) * 1968-05-31 1971-11-09 Int Nickel Co Cast nickel-base alloy
JPS4953121A (en) * 1972-07-26 1974-05-23
FR2220589A1 (en) * 1973-03-10 1974-10-04 Deutsche Edelstahlwerke Gmbh
US3869284A (en) * 1973-04-02 1975-03-04 French Baldwin J High temperature alloys
USRE28681E (en) * 1973-04-02 1976-01-13 High temperature alloys
USRE29920E (en) * 1975-07-29 1979-02-27 High temperature alloys
US4174964A (en) * 1969-10-28 1979-11-20 The International Nickel Company, Inc. Nickel-base alloys of improved high temperature tensile ductility
US4205985A (en) * 1978-03-02 1980-06-03 National Research Institute For Metals Nickel base alloy
FR2478128A1 (en) * 1980-03-13 1981-09-18 Rolls Royce Nickel alloy for single crystal casting - contg. chromium, cobalt, titanium, aluminium, tungsten, niobium, tantalum, and carbon
FR2513269A1 (en) * 1981-09-19 1983-03-25 Rolls Royce COMPOSITION AND THERMAL TREATMENT FOR ALLOY FOR MONOCRYSTALLINE MOLDINGS
US4629521A (en) * 1984-12-10 1986-12-16 Special Metals Corporation Nickel base alloy
US4861547A (en) * 1988-04-11 1989-08-29 Carondelet Foundry Company Iron-chromium-nickel heat resistant alloys
US6632299B1 (en) 2000-09-15 2003-10-14 Cannon-Muskegon Corporation Nickel-base superalloy for high temperature, high strain application
WO2009094271A1 (en) * 2008-01-23 2009-07-30 Force Protection Technologies, Inc. Apparatus for defeating high energy projectiles
US20090293709A1 (en) * 2008-05-27 2009-12-03 Joynt Vernon P Apparatus for defeating high energy projectiles
DE102017131206A1 (en) 2016-12-23 2018-06-28 Caterpillar Inc. HIGH-TEMPERATURE ALLOY FOR PURPOSING MOTOR VALVES
US11761060B2 (en) 2018-12-04 2023-09-19 Alloyed Limited Nickel-based alloy
US11859267B2 (en) 2016-10-12 2024-01-02 Oxford University Innovation Limited Nickel-based alloy

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2587275A (en) * 1949-09-23 1952-02-26 Driver Harris Co Furnace element
GB710413A (en) * 1951-03-15 1954-06-09 Mond Nickel Co Ltd Improvements relating to alloys
US2920956A (en) * 1956-10-08 1960-01-12 Universal Cyclops Steel Corp Method of preparing high temperature alloys
US2948606A (en) * 1957-05-31 1960-08-09 Sierra Metals Corp High temperature nickel base alloy
US2951757A (en) * 1958-03-07 1960-09-06 Westinghouse Electric Corp High temperature nickel base alloy

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2587275A (en) * 1949-09-23 1952-02-26 Driver Harris Co Furnace element
GB710413A (en) * 1951-03-15 1954-06-09 Mond Nickel Co Ltd Improvements relating to alloys
US2920956A (en) * 1956-10-08 1960-01-12 Universal Cyclops Steel Corp Method of preparing high temperature alloys
US2948606A (en) * 1957-05-31 1960-08-09 Sierra Metals Corp High temperature nickel base alloy
US2951757A (en) * 1958-03-07 1960-09-06 Westinghouse Electric Corp High temperature nickel base alloy

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3322534A (en) * 1964-08-19 1967-05-30 Int Nickel Co High temperature nickel-chromium base alloys
US3403059A (en) * 1965-06-24 1968-09-24 Gen Electric Nickel base alloy
US3508917A (en) * 1966-08-15 1970-04-28 Int Nickel Co Alloy for gas reformer tubes
US3459545A (en) * 1967-02-20 1969-08-05 Int Nickel Co Cast nickel-base alloy
US3473922A (en) * 1967-07-21 1969-10-21 Carondelet Foundry Co Corrosion-resistant alloys
US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties
US3617261A (en) * 1968-02-08 1971-11-02 Cyclops Corp Specialty Steel D Wrought nickel base superalloys
US3619182A (en) * 1968-05-31 1971-11-09 Int Nickel Co Cast nickel-base alloy
US4174964A (en) * 1969-10-28 1979-11-20 The International Nickel Company, Inc. Nickel-base alloys of improved high temperature tensile ductility
JPS4953121A (en) * 1972-07-26 1974-05-23
FR2220589A1 (en) * 1973-03-10 1974-10-04 Deutsche Edelstahlwerke Gmbh
US3869284A (en) * 1973-04-02 1975-03-04 French Baldwin J High temperature alloys
USRE28681E (en) * 1973-04-02 1976-01-13 High temperature alloys
USRE29920E (en) * 1975-07-29 1979-02-27 High temperature alloys
US4205985A (en) * 1978-03-02 1980-06-03 National Research Institute For Metals Nickel base alloy
FR2478128A1 (en) * 1980-03-13 1981-09-18 Rolls Royce Nickel alloy for single crystal casting - contg. chromium, cobalt, titanium, aluminium, tungsten, niobium, tantalum, and carbon
FR2513269A1 (en) * 1981-09-19 1983-03-25 Rolls Royce COMPOSITION AND THERMAL TREATMENT FOR ALLOY FOR MONOCRYSTALLINE MOLDINGS
US4629521A (en) * 1984-12-10 1986-12-16 Special Metals Corporation Nickel base alloy
US4861547A (en) * 1988-04-11 1989-08-29 Carondelet Foundry Company Iron-chromium-nickel heat resistant alloys
US6632299B1 (en) 2000-09-15 2003-10-14 Cannon-Muskegon Corporation Nickel-base superalloy for high temperature, high strain application
WO2009094271A1 (en) * 2008-01-23 2009-07-30 Force Protection Technologies, Inc. Apparatus for defeating high energy projectiles
US20090293709A1 (en) * 2008-05-27 2009-12-03 Joynt Vernon P Apparatus for defeating high energy projectiles
US11859267B2 (en) 2016-10-12 2024-01-02 Oxford University Innovation Limited Nickel-based alloy
DE102017131206A1 (en) 2016-12-23 2018-06-28 Caterpillar Inc. HIGH-TEMPERATURE ALLOY FOR PURPOSING MOTOR VALVES
US10533240B2 (en) 2016-12-23 2020-01-14 Caterpillar Inc. High temperature alloy for casting engine valves
US10865466B2 (en) 2016-12-23 2020-12-15 Caterpillar Inc. High temperature alloy for casting engine valves
US11761060B2 (en) 2018-12-04 2023-09-19 Alloyed Limited Nickel-based alloy

Similar Documents

Publication Publication Date Title
US3164465A (en) Nickel-base alloys
US3832167A (en) Nickel alloy with good stress-rupture strength
JP3027200B2 (en) Oxidation resistant low expansion alloy
US3030206A (en) High temperature chromiummolybdenum alloy
US4386976A (en) Dispersion-strengthened nickel-base alloy
US3922168A (en) Intermetallic compound materials
US3366478A (en) Cobalt-base sheet alloy
US3343950A (en) Nickel-chromium alloys useful in the production of wrought articles for high temperature application
JPS6115135B2 (en)
US3723108A (en) Nickel-chromium-cobalt alloys
US3322534A (en) High temperature nickel-chromium base alloys
US3027255A (en) High strength niobium base alloys
US3118763A (en) Cobalt base alloys
US3668023A (en) Tantalum-containing precipitation-strengthened nickel-base alloy
US2975051A (en) Nickel base alloy
US3177076A (en) Forgeable high temperature cast alloys
US2960403A (en) Molybdenum-base alloys
US3113863A (en) Columbium base alloy
US3069258A (en) Nickel-chromium casting alloy with niobides
US2974036A (en) High temperature cobalt-base alloy
US3597193A (en) Vanadium base alloy
US3089769A (en) Nickel-chromium-palladium brazing alloy
US2974037A (en) High temperature cobalt base alloy
US3026199A (en) Metal alloy
US3707409A (en) Nickel base alloy