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US2793950A - Heat-resistant nickel-base sheet alloy - Google Patents

Heat-resistant nickel-base sheet alloy Download PDF

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US2793950A
US2793950A US365854A US36585453A US2793950A US 2793950 A US2793950 A US 2793950A US 365854 A US365854 A US 365854A US 36585453 A US36585453 A US 36585453A US 2793950 A US2793950 A US 2793950A
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alloy
titanium
aluminum
iron
molybdenum
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US365854A
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Italo S Servi
Jr Howard R Spendelow
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Union Carbide Corp
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Union Carbide and Carbon Corp
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%

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  • This invention relates to heat-resistant boron-free, nickel-base alloys capable of being rolled into sheet. More specifically, this invention relates to such nickelbase alloys having high stress-rupture properties and articles made therefrom.
  • the alloy of the invention is boron-free and has the composition 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum, 2.25% to 5.0% titanium, 1.75% to 2.50% aluminum, 0.08% to 0.25% carbon, remainder nickel and incidental impurities.
  • a preferred composition is within the following limits: 14% to 16% chromium, 8% to 12% iron, to 6% molybdenum, 2.25% to 4% titanium, 1.75% to 2.25% aluminum, 0.12% to 0.16% carbon, remainder nickel and incidental impurities.
  • Fig. 1 is a curve graphically illustrating the effect of the iron content on the stress-rupture life of the alloys of the invention.
  • Fig. 2 is a curve graphically illustrating the effect of the molybdenum content on the stress-rupture life of the alloys of the invention.
  • the alloy of the invention is closely balanced and the ranges listed are critical.
  • the desirable properties of the alloy of the invention arise from close balancing, the balancing representing a compromise between high stress-rupture properties and the ability of being rolled into sheet.
  • the inter-relationship of the alloying elements to each other, in the ranges set forth, gives rise to the distinguishing characteristics of the alloy. For example, not only are the proportions of the elements chromium, molybdenum and iron present in the alloy of the invention individually critical to the attainment of the desired properties, but they are critically interrelated with respect to each other.
  • Fig. 1 is a graphic representation of stress-rupture life of the alloy of the invention at 1600" F. using 20,000 pounds per square inch.
  • the iron content was varied, as shown in the graph, in an alloy having the composition: 15% to 16% chromium, about 5.5% molybdenum, 1.80% to 2.25% aluminum, 2.50% to 2.75% titanium, 0.12% to 0.15% carbon, balance nickel and incidental impurities.
  • An examination of the graph points out the close balancing and criticality of the iron content in the alloy of the invention.
  • the maximum stress-rupture life of about 400 hours is reached in a narrow range of iron, a reduction in iron content to below this range serves to reduce the stress-rupture life sharply, for example, the stress-rupture life is shortened by about one-fourth for one hundred hours, if the iron content is reduced to about 6%.
  • the significance of the close balancing and criticality is even more sharply noted if the iron content is increased beyond its narrow range, for example, the stress-rupture life is shortened by about onehalf, or two hundred hours, if the iron content is increased about 6% beyond its narrow range.
  • Fig. 2 is a graphic representation of stressrupture life of the alloy of the invention at 1500 F. using 35,000 pounds per square inch.
  • the molybdenum content was varied, as shown in the graph, in an alloy having the composition: 15% to 16% chromium, about 8.5% iron, 1.75% to 2.25% aluminum, 2.50% to 2.75% titanium, 0.11% to 0.16% carbon, balance nickel and incidental impurities.
  • An examination of the graph points out the close balancing and criticality of the molybdenum content in the alloy of the invention, it is to be noted, to an even closer degree than that of the iron content.
  • the maximum stressrupture life of about hours is reached in an extremely narrow range of molybdenum, a reduction in molybdenum content to below this range serves to reduce the stress-rupture life with remarkable sharpness, for example, the stress-rupture life is shortened by greater than two-thirds, or about one hundred and twenty-five hours, if the molybdenum content is reduced by about 3%.
  • the significance of the close balancing and criticality is also sharply noted if the molybdenum content is increased beyond its narrow range, for example, the stress-rupture life is shortened by about one-half, or ninety hours, if the molybdenum content is increased about 3%.
  • the amounts of aluminum and titanium in the alloy of the invention are no less critical than the other elements.
  • An increase in aluminum and titanium is beneficial to the strength of the alloy of the invention but impairs the hot-workability and cold-formability.
  • the ratio of titanium to aluminum is of particular importance; not only are the percentages listed for each of extreme importance, but their proportion to each other is also of great importance.
  • the amount of titanium is always in excess of the amount of aluminum, being present in a proportion to each other.
  • a preferred ratio is about l-l /z parts titanium to 1 part aluminum.
  • the distinguishing properties of the alloy is the constancy of yield strength from room temperature to expected operating temperatures.
  • the sharp break of other comparable alloys in yield strength serves to point out one of the distinctive advantages of the alloy of the invention.
  • Other distinguishing properties of the alloy of the invention are its hotworkability, room-temperature ductility and high temperature strength. Such properties permit the fabrication by hot working of sheet, bar stock, forgings, plates and articles for service at elevated temperatures under stress.
  • Another desirable property of the alloy of the invention that sets it apart from other comparable alloys is that no artificial aging treatment is necessaryy to develop stressrupture properties superior to properties of comparable current alloys.
  • the alloys of the invention are melted and cast in vacuo, as hereinafter set forth in detail, regardless of the amount of the alloying metals within their stated ranges.
  • Vacuum melting and casting consistently produce sound ingots that can be rolled Without difiiculty.
  • the alloy may be produced by melting in air in the conventional manner with certain requirements such as casting in a sand mold as set forth hereinafter. If the titanium content exceeds about 2 /2% to 3%, vacuum melting and casting must be employed.
  • a preferred method is to charge all material into the furnace using an excess of carbon.
  • the furnace is partially evacuated and the charge is melted.
  • the power is reduced to an amount sufficient to maintain the charge in a molten state and the pressure reduced slowly, exercising care to prevent a violent boil, during which time the excess carbon is reacting with the impurities in the charge.
  • the reaction can be retarded by increasing the chamber pressure with argon.
  • the pressures should finally be reduced to about 0.3 mm. to 0.5 mm. and then temperature and pressure are held constant until apparent reaction ceases, after which the heat is poured in a partial atmosphere of argon.
  • the alloy When the air-melting technique is used, the alloy is melted in conventional manner in air exercising the usual precautions. When melted, the alloy is cast into a sand mold provided with a hot top.
  • An exothermic hot-topping compound for example, that commercially available under designation Thermotomic No. 2, manufactured by Pittsburgh Metals Purifying Co., Pittsburgh, Pa., should be placed in the hot top.
  • Thermotomic No. 2 manufactured by Pittsburgh Metals Purifying Co., Pittsburgh, Pa.
  • the alloy After casting of the alloy of the invention by either method above set forth, the alloy is hot-worked in a temperature range of 1050 C. to 1180 C.
  • Heat No. A was prepared by the air-melting technique before set forth, and beat No. B was prepared by the vacuum melting technique before set forth. Attention is directed to the exceptional rupture life of 167.7 hours at 1800" F. with a load of 10,000 pounds per square inch for heat B, demonstrating one of the distinguishing characteristics of the alloy of the invention.
  • the outstanding properties of the alloy of the invention recommend its use for fabrication by hot-working by rolling into sheet material or by other means of severe hot-working to form turbine buckets, tail cones for jet aircraft, valves or parts thereof, or the like; in short, for metal or metal articles for use at high temperatures under stress.
  • a boron-free, nickel-base alloy capable of being rolled into sheet consisting essentially of 15% to 17% chromium, 8% to 12% iron, 4% to molybdenum, titanium and aluminum in a ratio of about 1 /1 parts titanium to 1 part aluminum, the titanium being present in a range from 2.25% to 5.0%, 0.08% to 0.25% carbon, remainder nickel and incidental impurities.
  • a boron-free, nickel-base alloy capable of being rolled into sheet consisting essentially of 14% to 16% chromium, 8% to 12% iron, 5% to 6% molybdenum, 2.25% to 4% titanium, 1.75% to 2.25% aluminum, 0.12% to 0.16% carbon, remainder nickel and incidental impurities.
  • a boron-free, nickel-base alloy capable of being rolled into sheet consisting essentially of 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum. 2.25% to 5.0% titanium, 1.75% to 2.50% aluminum, up to 2.5% cobalt, 0.08% to 0.25% carbon, remainder nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to 1 and 1.5 to l.
  • a heat-resistant, hot-workable boron-free, nickelbase alloy capable of being fabricatzd into bar stock, consisting essentially of 14% to 17% chromium. 8% to 12% iron, 4% to 7% molybdenum, 2.25% to 5.0% titanium, 0.08% to 0.25% carbon, remainder aluminum, nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to l and 1.5 to 1.
  • Boron-free, nickel-base article having essentially the composition 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum. 2.25% to 5.0% titanium. 1.75% to 2.5 0% aluminum, 0.08% to 0.25% carbon. balance nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to 1 and 1.5 to l.
  • a nickel-base alloy exhibiting high strength characteristics and hot-workability and cold formability properties, in the absence of boron therein, said alloy consisting essentially of 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum, 1.75% to 2.50% aluminum, 0.08% to 0.25% carbon, remainder titanium, nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to 1 and 1.5 to 1.
  • the method of imparting hot workability and cold formability prop erties which comprises incorporating titanium and aluminum in said alloy, regulating the ratio of said titanium to said aluminum between 1.0 to 1 and 1.5 to 1. excluding the embodiment of boron therein while restricting the alloy composition to 14% to 17% chromium. 8% to 12% iron, 4% to 7% molybdenum. 2.25% to 5.0% titanium, 1.75% to 2.50% aluminum, 0.08% to 0.25 carbon, remainder nickel and incidental impurities.

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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)

Description

May 28, 1957 l. s. SERVI ETAL 2,793,950
HEAT-RESISTANT NICKELBASE SHEET ALLOY Filed July 3, 1955 a n m On n u 3 0 n 3 In a. on H l m cm n0 5 Q. on om 00. ccm v 3m aunldna sanou semi R. SPEN ELOW,JR. 9.
INVENTOR ITALO 8 ATTORNEY United States Patent HEAT-RESISTANT NICKEL-BASE SHEET ALLOY Italo S. Servi, Niagara Falls, and Howard R. Spendelow, Jr., Snyder, N. Y., assignors to Union Carbide and Carbon Corporation, a corporation of New York Application July a, 1953, Serial No. 365,854
8 Claims. (Cl. 75-171 This invention relates to heat-resistant boron-free, nickel-base alloys capable of being rolled into sheet. More specifically, this invention relates to such nickelbase alloys having high stress-rupture properties and articles made therefrom.
The increasing demand in the aeronautical fields for alloys having stress-resistance at high temperatures, particularly in jet engine design, is constantly paced by the restrictions of the so-called strategic metals. As jet engines develop, they tend to feed more and more upon the metals that are less and less available, columbium, tantalum, tungsten, cobalt being the metals currently in use. It would be greatly desirable to have available an alloy of the required properties for such use, but that utilizes a minimum, or none, of these strategic metals.
It is the object of this invention to provide a heatresistant alloy, comprising a boron-free, nickel-base alloy containing chromium, iron, molybdenum, titanium, aluminum and carbon, that can be hot-worked into sheet, bars and articles that have high stress-rupture properties.
The alloy of the invention is boron-free and has the composition 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum, 2.25% to 5.0% titanium, 1.75% to 2.50% aluminum, 0.08% to 0.25% carbon, remainder nickel and incidental impurities. A preferred composition is within the following limits: 14% to 16% chromium, 8% to 12% iron, to 6% molybdenum, 2.25% to 4% titanium, 1.75% to 2.25% aluminum, 0.12% to 0.16% carbon, remainder nickel and incidental impurities.
In the accompanying drawings:
Fig. 1 is a curve graphically illustrating the effect of the iron content on the stress-rupture life of the alloys of the invention; and
Fig. 2 is a curve graphically illustrating the effect of the molybdenum content on the stress-rupture life of the alloys of the invention.
The alloy of the invention is closely balanced and the ranges listed are critical. The desirable properties of the alloy of the invention arise from close balancing, the balancing representing a compromise between high stress-rupture properties and the ability of being rolled into sheet. The inter-relationship of the alloying elements to each other, in the ranges set forth, gives rise to the distinguishing characteristics of the alloy. For example, not only are the proportions of the elements chromium, molybdenum and iron present in the alloy of the invention individually critical to the attainment of the desired properties, but they are critically interrelated with respect to each other.
The accompanying drawings serve to illustrate clearly the criticality of the ranges of the alloying elements.
Fig. 1 is a graphic representation of stress-rupture life of the alloy of the invention at 1600" F. using 20,000 pounds per square inch. The iron content was varied, as shown in the graph, in an alloy having the composition: 15% to 16% chromium, about 5.5% molybdenum, 1.80% to 2.25% aluminum, 2.50% to 2.75% titanium, 0.12% to 0.15% carbon, balance nickel and incidental impurities. An examination of the graph points out the close balancing and criticality of the iron content in the alloy of the invention. The maximum stress-rupture life of about 400 hours is reached in a narrow range of iron, a reduction in iron content to below this range serves to reduce the stress-rupture life sharply, for example, the stress-rupture life is shortened by about one-fourth for one hundred hours, if the iron content is reduced to about 6%. The significance of the close balancing and criticality is even more sharply noted if the iron content is increased beyond its narrow range, for example, the stress-rupture life is shortened by about onehalf, or two hundred hours, if the iron content is increased about 6% beyond its narrow range.
Further pointing out the criticality of the ranges of the alloying elements, Fig. 2 is a graphic representation of stressrupture life of the alloy of the invention at 1500 F. using 35,000 pounds per square inch. The molybdenum content was varied, as shown in the graph, in an alloy having the composition: 15% to 16% chromium, about 8.5% iron, 1.75% to 2.25% aluminum, 2.50% to 2.75% titanium, 0.11% to 0.16% carbon, balance nickel and incidental impurities. An examination of the graph points out the close balancing and criticality of the molybdenum content in the alloy of the invention, it is to be noted, to an even closer degree than that of the iron content. The maximum stressrupture life of about hours is reached in an extremely narrow range of molybdenum, a reduction in molybdenum content to below this range serves to reduce the stress-rupture life with remarkable sharpness, for example, the stress-rupture life is shortened by greater than two-thirds, or about one hundred and twenty-five hours, if the molybdenum content is reduced by about 3%. The significance of the close balancing and criticality is also sharply noted if the molybdenum content is increased beyond its narrow range, for example, the stress-rupture life is shortened by about one-half, or ninety hours, if the molybdenum content is increased about 3%.
To recapitulate, in view of the accompanying graphs, the significance of the careful adjustment of the proportions of the alloying elements in the alloy of the invention and their narrowly restricted amounts are seen to be of paramount importance in achieving the physical properties that give to the alloy of the invention its distinguishing characteristics.
The amounts of aluminum and titanium in the alloy of the invention are no less critical than the other elements. An increase in aluminum and titanium is beneficial to the strength of the alloy of the invention but impairs the hot-workability and cold-formability. Moreover, the ratio of titanium to aluminum is of particular importance; not only are the percentages listed for each of extreme importance, but their proportion to each other is also of great importance. In any given composition the amount of titanium is always in excess of the amount of aluminum, being present in a proportion to each other. A preferred ratio is about l-l /z parts titanium to 1 part aluminum.
Among the distinguishing properties of the alloy is the constancy of yield strength from room temperature to expected operating temperatures. The sharp break of other comparable alloys in yield strength serves to point out one of the distinctive advantages of the alloy of the invention. Other distinguishing properties of the alloy of the invention are its hotworkability, room-temperature ductility and high temperature strength. Such properties permit the fabrication by hot working of sheet, bar stock, forgings, plates and articles for service at elevated temperatures under stress. Another desirable property of the alloy of the invention that sets it apart from other comparable alloys is that no artificial aging treatment is necesary to develop stressrupture properties superior to properties of comparable current alloys.
Preferably, the alloys of the invention are melted and cast in vacuo, as hereinafter set forth in detail, regardless of the amount of the alloying metals within their stated ranges. Vacuum melting and casting consistently produce sound ingots that can be rolled Without difiiculty. However, if the titanium content is on the low side of the range listed, the alloy may be produced by melting in air in the conventional manner with certain requirements such as casting in a sand mold as set forth hereinafter. If the titanium content exceeds about 2 /2% to 3%, vacuum melting and casting must be employed.
When the vacuum melting technique is used, a preferred method is to charge all material into the furnace using an excess of carbon. The furnace is partially evacuated and the charge is melted. When the charge is molten, the power is reduced to an amount sufficient to maintain the charge in a molten state and the pressure reduced slowly, exercising care to prevent a violent boil, during which time the excess carbon is reacting with the impurities in the charge. (The reaction can be retarded by increasing the chamber pressure with argon.) The pressures should finally be reduced to about 0.3 mm. to 0.5 mm. and then temperature and pressure are held constant until apparent reaction ceases, after which the heat is poured in a partial atmosphere of argon.
When the air-melting technique is used, the alloy is melted in conventional manner in air exercising the usual precautions. When melted, the alloy is cast into a sand mold provided with a hot top. An exothermic hot-topping compound, for example, that commercially available under designation Thermotomic No. 2, manufactured by Pittsburgh Metals Purifying Co., Pittsburgh, Pa., should be placed in the hot top. By exercising these precautions, a sound ingot substantially free of objectionable inclusions is produced. Clean, sound ingots of 6 x 6 x 40 inches have been successfully made by this method.
After casting of the alloy of the invention by either method above set forth, the alloy is hot-worked in a temperature range of 1050 C. to 1180 C.
The following data show the excellent physical properties of specific examples of the alloy of the invention. Heat No. A was prepared by the air-melting technique before set forth, and beat No. B was prepared by the vacuum melting technique before set forth. Attention is directed to the exceptional rupture life of 167.7 hours at 1800" F. with a load of 10,000 pounds per square inch for heat B, demonstrating one of the distinguishing characteristics of the alloy of the invention.
Heat N A B Composition:
Percent Chromium.. Percent Iron Percent lilolybdenum. Percent Titanium Percent Aluminurm. Percent Carboiu.
.. Pr t r-s e Autographic stress strain: 0.109-inch hot-rolled, mill-annealed I sheet Stress rupture data: 0.25-inch hot-rolled mill-annealed round.
Heat No. B
Rupture Elonga Lift, tion, Hr Percent.
151. 8 l0. 2 226. 8 7. 4 285. 1 14. it 338. 0 14. 9 107. 7 35. 8
l Mill-annealed-heated at 2150 F. and air-cooled.
The outstanding properties of the alloy of the invention recommend its use for fabrication by hot-working by rolling into sheet material or by other means of severe hot-working to form turbine buckets, tail cones for jet aircraft, valves or parts thereof, or the like; in short, for metal or metal articles for use at high temperatures under stress.
What is claimed is:
l. A boron-free, nickel-base alloy capable of being rolled into sheet consisting essentially of 15% to 17% chromium, 8% to 12% iron, 4% to molybdenum, titanium and aluminum in a ratio of about 1 /1 parts titanium to 1 part aluminum, the titanium being present in a range from 2.25% to 5.0%, 0.08% to 0.25% carbon, remainder nickel and incidental impurities.
2. A boron-free, nickel-base alloy capable of being rolled into sheet consisting essentially of 14% to 16% chromium, 8% to 12% iron, 5% to 6% molybdenum, 2.25% to 4% titanium, 1.75% to 2.25% aluminum, 0.12% to 0.16% carbon, remainder nickel and incidental impurities.
3. A boron-free, nickel-base alloy capable of being rolled into sheet consisting essentially of 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum. 2.25% to 5.0% titanium, 1.75% to 2.50% aluminum, up to 2.5% cobalt, 0.08% to 0.25% carbon, remainder nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to 1 and 1.5 to l.
4. A heat-resistant, hot-workable boron-free, nickelbase alloy, capable of being fabricatzd into bar stock, consisting essentially of 14% to 17% chromium. 8% to 12% iron, 4% to 7% molybdenum, 2.25% to 5.0% titanium, 0.08% to 0.25% carbon, remainder aluminum, nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to l and 1.5 to 1.
5. Boron-free, nickel-base article having essentially the composition 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum. 2.25% to 5.0% titanium. 1.75% to 2.5 0% aluminum, 0.08% to 0.25% carbon. balance nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to 1 and 1.5 to l.
6. A nickel-base alloy exhibiting high strength characteristics and hot-workability and cold formability properties, in the absence of boron therein, said alloy consisting essentially of 14% to 17% chromium, 8% to 12% iron, 4% to 7% molybdenum, 1.75% to 2.50% aluminum, 0.08% to 0.25% carbon, remainder titanium, nickel and incidental impurities, the ratio of titanium to aluminum being between 1.0 to 1 and 1.5 to 1.
7. In the art of manufacturing nickel-base alloy for high temperature use of the type normally containing boron, chromium, molybdenum and iron, the method of imparting hot workability and cold formability prop erties, which comprises incorporating titanium and aluminum in said alloy, regulating the ratio of said titanium to said aluminum between 1.0 to 1 and 1.5 to 1. excluding the embodiment of boron therein while restricting the alloy composition to 14% to 17% chromium. 8% to 12% iron, 4% to 7% molybdenum. 2.25% to 5.0% titanium, 1.75% to 2.50% aluminum, 0.08% to 0.25 carbon, remainder nickel and incidental impurities.
8. A nickel-base alloy characterized by high tempera ture strength and by hot workability and cold formabil ty consisting of 14% to 17% chromium, 2.25% to 5.0% titanium, 1.75% to 2.50% aluminum, 0.08% to 0.25% carbon and the remainder nickel, molybdenum, iron and incidental impurities, said molybdenum and iron being critically balanced in amounts between 4% and 7% and between 8% and 12%, respectively, for imparting peak rupture life without afiecting the workability and formability of said alloy, the ratio of titanium to aluminum being between 1.0 to 1 and 1.5 to 1.
Franks et a1. Dec. 16, 1947 Bieber et a1. July 18, 1950 FOREIGN PATENTS Australia Dec. 17, 1941 Australia Oct. 26, 1949

Claims (2)

  1. 2. A BORON-FREE, NICKLE-BASE ALLOY CAPABLE OF BEING ROLLED INTO SHEET CONSISTING ESSENTIALLY OF 14% TO 16% CHROMIUM, 8% TO 12% IRON 5% TO 6% MOLYBDENUM, 2.25% TO 4% TITANIUM, 1.75% TO 2.25% ALUMINUM, 0.12% TO 0.16% CARBON, REMAINDER NICKLE AND INCIDENTAL IMPURITIES.
  2. 7. IN THE ART OF MANUFACTURING NICKLE-BASE ALLOY FOR HIGH TEMPERATURE USE OF THE TYPE NORMALLY CONTAINING BORON, CHROMIUM MOLYBDENUM AND IRON, THE METHOD OF IMPAIRING HOT WORKABILITY AND COLD FORMABILITY PROPERTIES, WHICH COMPRISES INCORPORATING TITANIUM AND ALUMINUM IN SAID ALLOY, REGULATING THE RATIO OF SAID TITANIUM TO SAID ALUMINUM BETWEEN 1.0 TO 1 AND 1.5 TO 1, EXCLUDING THE EMBODIMENT OF BORON THEREIN WHILE RESTRICTING THE ALLOY COMPOSITION TO 14% TO 17% CHROMIUM, 8% TO 12% IRON 4% TO 7% MOLYBDENUM, 2,25% TO 5.0% TITANIUM, 1.75% TO 2.50% ALUMINUM, 0.08% TO 0.25% CARBON, REMINDER NICKLE AND INCIDENTAL IMPURITIES.
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060051234A1 (en) * 2004-09-03 2006-03-09 Pike Lee M Jr Ni-Cr-Co alloy for advanced gas turbine engines
US20060222557A1 (en) * 2004-09-03 2006-10-05 Pike Lee M Jr Ni-Cr-Co alloy for advanced gas turbine engines

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU134904B (en) * 1904-08-22 1905-08-29 Shearcroft Mollen Robert Improved butter cutting or sizing machine
US2432619A (en) * 1946-05-09 1947-12-16 Haynes Stellite Co Ferrous alloys and articles
US2515185A (en) * 1943-02-25 1950-07-18 Int Nickel Co Age hardenable nickel alloy

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU134904B (en) * 1904-08-22 1905-08-29 Shearcroft Mollen Robert Improved butter cutting or sizing machine
US2515185A (en) * 1943-02-25 1950-07-18 Int Nickel Co Age hardenable nickel alloy
US2432619A (en) * 1946-05-09 1947-12-16 Haynes Stellite Co Ferrous alloys and articles

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060051234A1 (en) * 2004-09-03 2006-03-09 Pike Lee M Jr Ni-Cr-Co alloy for advanced gas turbine engines
US20060222557A1 (en) * 2004-09-03 2006-10-05 Pike Lee M Jr Ni-Cr-Co alloy for advanced gas turbine engines
US8066938B2 (en) 2004-09-03 2011-11-29 Haynes International, Inc. Ni-Cr-Co alloy for advanced gas turbine engines

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