US3030206A - High temperature chromiummolybdenum alloy - Google Patents

High temperature chromiummolybdenum alloy Download PDF

Info

Publication number
US3030206A
US3030206A US793935A US79393559A US3030206A US 3030206 A US3030206 A US 3030206A US 793935 A US793935 A US 793935A US 79393559 A US79393559 A US 79393559A US 3030206 A US3030206 A US 3030206A
Authority
US
United States
Prior art keywords
alloy
chromium
molybdenum
silicon
oxidation resistance
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
US793935A
Inventor
Jr Ronald Horace Buck
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 Motors Liquidation Co filed Critical Motors Liquidation Co
Priority to US793935A priority Critical patent/US3030206A/en
Application granted granted Critical
Publication of US3030206A publication Critical patent/US3030206A/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
    • C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade

Definitions

  • the nickel base alloy and cobalt base alloy blades commonly used today in gas turbine engines for aircraft normally have maximum service temperatures of approximately 1800 F. to 1900 F. This limitation necessarily restricts the performance and efiiciency of these engines.
  • Refractory metals such asniobium, tungsten, molybdenum and chromium, have satisfactory high melting temperatures and sufiicient potential availability to warrant investigation as high temperature turbine blade materials.
  • each of these metals exhibits poor oxidation resistance at temperatures of 2000 F. or above. Therefore, such metals are unsatisfactory for use in turbine blades which necessarily are exposed to extremely hot oxidizing gases.
  • attempts have been made to correct this deficiency by adding small amounts of various alloying elements to these refractory base metals. However, these attempts have been unsuccessful since the resultant products still did not possess adequate oxidation resistance at the very high temperatures under consideration.
  • a principal object of the present invention is to provide a refractory alloy which can be employed as a turbine blade material at temperatures upto 2000 F. because of its outstanding oxidation resistance at such temperatures, coupled with good hot strength and other necessary physical properties.
  • Such an alloy should possess adequate fabricability and a melting point of at least 3000 F. It is preferable that turbine blades formed of this alloy have an oxide scale thickness of not more than 0.005 inch after 100 hours exposure in air at a temperature of 2000 F.
  • an alloy comprising about 45% to 70% chromium and 30% to 55% molybdenum satisfies the foregoing requirements to a greater extent than the refractory alloys heretofore known.
  • a chromium content of 50% to 61% appears to provide most advantageous results, particularly with respect to the combination of oxidation resistance and hot strength.
  • an alloy composed solely of 60% chromium and 40% molybdenum produces an oxide coating having a thickness of 0.01 inch after 100 hours exposure at a temperature of 2000" F.
  • a silicon-containing chromium-molybdenum alloy having a chromium content measurably'less than 60% it is desirable to include at least 0.1% silicon and preferably 0.2% silicon to achieve adequate resistance to high temperature oxidation.
  • the latter amount of silicon is required for best results if other minor constituents are not added.
  • As little as 0.01% silicon has been found to appreciably improve the oxidation resistance of the higher chromium content alloys. Likewise some improvement in this property is produced with only 0.02% calcium.
  • chromium-molybdenum alloy Small amounts of various elements can be tolerated in the chromium-molybdenum alloy without detriment to its physical properties. For example, if arsenic, manganese, aluminum, titanium, tantalum and thorium or boron is present in the binary alloy as the only minor constituent, less than 1% of such an element does not significantly affect the high temperature oxidation resistance of the alloy. However, combination additions of small quantities of silicon plus aluminum, silicon plus aluminum and titanium, calcium pins mischmetal, and calcium plus arsenic and mischmetal prevent the average thickness of the oxide scale formed on the chromium-molybdenum alloy from exceeding 0.005 inch after hours cyclic exposure to air at a temperature of about 2000 F.
  • deoxidizing additions may be beneficially made. These intergranular impurities appear to be reduced to the greatest extent by the addition of 0.05% titanium and 0.1% to 0.3% calcium.
  • Sound extrusions may be obtained with the chromiummolybdenum alloy by first hot pressing it to approximately 10% reduction in thickness at a temperature of 3150 F. Initial hot working produces a wrought recrystallized structure which enables the alloy to be further hot worked, such as by extrusion.
  • a molybdenum alloy containing more than about 25% chromium l acked suitable high temperature oxidation resistance and could not be worked without cracking.
  • the alloy described herein has excellent oxidation resistance and can be suitably hot worked.
  • the alloy composed of 50.2% chromium, 48.8%.molybdenum, 0.5% silicon and 0.5% aluminum and the alloy containing 50% chromium, 47% molybdenum and 3% silicon were found to have melting points between 3200 F. and 3300 P.
  • the refractory alloys described herein all were prepared by non-consumable arc-melting in an inert atmosphere of argon plus helium. Raw materials of maximum available purity were used. The constituents of the alloys may be added either simultaneously or successively.
  • a chromium-molybdenum alloy having an oxide scale thickness of not in excess of about 0.005 inch after 100 hours exposure in air at a temperature of 2000 F., said alloy consisting essentially of about 45% to 70% chromium, 0.1% to 3% silicon and the balance substantially molybdenum.
  • An alloy characterized by high oxidation resistance at a temperature of 2000 F. said alloy consisting essentially of about 50% to 61% chromium, 39% to 50% molybdenum, silicon not in excess of 3%, and aluminum not in excess of 0.5%, the amount of silicon and aluminum present being sufficient to materially increase the oxidation resistance of said alloy at 2000 F.
  • An alloy having high oxidation resistance at elevated temperatures consisting essentially of about 50% to 61% chromium, 39% to 50% molybdenum, silicon not in excess of 3%, aluminum not in excess of 0.5% and titanium not in excess of 0.5%, said a silicon, aluminum and titanium being present in amounts posed of approximately 62.4% chromium, 37.4% molybdenum, 0.17 %silicon and 0.03% aluminum was ruptured under the same test conditions.
  • An alloy consisting essentially of about 45% to 70% chromium, 30% to molybdenum, and a small amount effective to materially increase the high temperature oxidation resistance of said alloy of atleast one readily oxidizable member selected from the group consisting of silicon, aluminum, titanium, calcium, arsenic and mischmetal.
  • a gas turbine blade characterized by outstanding oxidation resistance upon exposure to oxidizing gases at a temperature of 2000 F., said blade being formed of an alloy consisting essentially of about 50% to 61% chromisufficient to materially increase the oxidation resistance of said alloy. at a temperature of 2000? F.
  • An oxidation-resistant alloy for use at extremely high temperatures consisting essentially of 50% to 61% chromium, calcium not in excess of 0.3%, mischmetal not in excess of 0.15%, and the balance substantially molybdenum, said calcium and mischmetal being present in amounts suflicient to prevent the formation of an oxide scale on said alloy having an average thickness in excess of about 0.005 inch after hours exposure to air at a temperature of 2000 F.
  • An alloy characterized by high oxidation resistance at a temperature of 2000 F. said alloy consisting essentially of 50% to 61% chromium, 39% to 50% molybdenum, calcium not in excess of 0.3%, arsenic not in excess of 0.08%, and mischmetal not in excess of 0.15 said calcium, arsenic and mischmetal being present in amounts effective to prevent the oxide scale on said alloy from having an average thicknessin excess' of about 0.005 inch after 100 hours exposure to air at a temperature of 2000 F.

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 Ofifice A 3,030,206 Patented Apr. 17, 1962 3,030,206 HIGH TEMPERATURE CHROMIUM- MOLYBDENUM ALLOY Ronald Horace Buck, Jr., Rochester, Mich., assignor to General Motors Corporation, Detroit, Mich, a corporation of Delaware No Drawing. Filed Feb. 17, 1959, Ser. No. 793,935 7 Claims. (Cl. 75-476) This invention relates to a chromium-molybdenum alloy having exceptionally high oxidation resistance at elevated temperatures. It pertains particularly to a refractory metal alloy of this type which is designed for buckets and vanes of gas turbine engines in which metal temperatures reach 2000 F.
The nickel base alloy and cobalt base alloy blades commonly used today in gas turbine engines for aircraft normally have maximum service temperatures of approximately 1800 F. to 1900 F. This limitation necessarily restricts the performance and efiiciency of these engines. Refractory metals, such asniobium, tungsten, molybdenum and chromium, have satisfactory high melting temperatures and sufiicient potential availability to warrant investigation as high temperature turbine blade materials. However, each of these metals exhibits poor oxidation resistance at temperatures of 2000 F. or above. Therefore, such metals are unsatisfactory for use in turbine blades which necessarily are exposed to extremely hot oxidizing gases. During recent years attempts have been made to correct this deficiency by adding small amounts of various alloying elements to these refractory base metals. However, these attempts have been unsuccessful since the resultant products still did not possess adequate oxidation resistance at the very high temperatures under consideration.
Accordingly, a principal object of the present invention is to provide a refractory alloy which can be employed as a turbine blade material at temperatures upto 2000 F. because of its outstanding oxidation resistance at such temperatures, coupled with good hot strength and other necessary physical properties. Such an alloy should possess adequate fabricability and a melting point of at least 3000 F. It is preferable that turbine blades formed of this alloy have an oxide scale thickness of not more than 0.005 inch after 100 hours exposure in air at a temperature of 2000 F.
In accordance with the present invention, I have found that an alloy comprising about 45% to 70% chromium and 30% to 55% molybdenum satisfies the foregoing requirements to a greater extent than the refractory alloys heretofore known. A chromium content of 50% to 61% appears to provide most advantageous results, particularly with respect to the combination of oxidation resistance and hot strength. For example, an alloy composed solely of 60% chromium and 40% molybdenum produces an oxide coating having a thickness of 0.01 inch after 100 hours exposure at a temperature of 2000" F.
Small but effective amounts of certain readily oxidizable elements and alloys, such as silicon, aluminum, titanium, calcium, arsenic and mischmetal, may be added to the binary alloy to further improve its extreme high temperature properties. In general, the maximum quantities of these addition agents which should be used to obtain optimum physical properties are approximately 3% silicon,
0.5% aluminum, 0.5% titanium, 0.3% calcium, 0.08% arsenic and 0.15% mischmetal.
With a silicon-containing chromium-molybdenum alloy having a chromium content measurably'less than 60%, it is desirable to include at least 0.1% silicon and preferably 0.2% silicon to achieve adequate resistance to high temperature oxidation. The latter amount of silicon is required for best results if other minor constituents are not added. However, as little as 0.01% silicon has been found to appreciably improve the oxidation resistance of the higher chromium content alloys. Likewise some improvement in this property is produced with only 0.02% calcium.
Small amounts of various elements can be tolerated in the chromium-molybdenum alloy without detriment to its physical properties. For example, if arsenic, manganese, aluminum, titanium, tantalum and thorium or boron is present in the binary alloy as the only minor constituent, less than 1% of such an element does not significantly affect the high temperature oxidation resistance of the alloy. However, combination additions of small quantities of silicon plus aluminum, silicon plus aluminum and titanium, calcium pins mischmetal, and calcium plus arsenic and mischmetal prevent the average thickness of the oxide scale formed on the chromium-molybdenum alloy from exceeding 0.005 inch after hours cyclic exposure to air at a temperature of about 2000 F.
When non-metallic inclusions are present in the grain boundaries of the alloy of this invention, deoxidizing additions may be beneficially made. These intergranular impurities appear to be reduced to the greatest extent by the addition of 0.05% titanium and 0.1% to 0.3% calcium.
Sound extrusions may be obtained with the chromiummolybdenum alloy by first hot pressing it to approximately 10% reduction in thickness at a temperature of 3150 F. Initial hot working produces a wrought recrystallized structure which enables the alloy to be further hot worked, such as by extrusion. Prior to the present invention, it had been thought that a molybdenum alloy containing more than about 25% chromium lacked suitable high temperature oxidation resistance and could not be worked without cracking. As indicated above, however, the alloy described herein has excellent oxidation resistance and can be suitably hot worked. l
' My tests have shown that silicon additions in amounts up to 3% greatly enhance the oxidation resistance of a 50% chromium-50% molybdenum alloy, and substantial improvement was obtained with an addition of only 0.2% silicon. The oxidation resistance of such an alloy was further benefited with the inclusion of 0.2% aluminum. For example, a 50% chromium-50% molybdenum alloy containing 0.2% silicon and 0.2% aluminum had an oxide layer thickness 0130.003 inch after 100 hours exposure at a temperature of 2000 F.
.In general, I found that a 60% chromium-40% molybdenum alloy is more resistant to oxidation at 2000 F. than a 50% chromium-50% molybdenum alloy. Oxidation resistance .of this higher chromium content alloy is further improved by the addition of 0.3% silicon plus 0.1% titanium and 0.1% aluminum. A 60% chromium- 40% molybdenum alloy containing 0.02% calcium, 0.08% arsenic and 0.15 mischmetal also had excellent high temperature oxidation resistance. In each instance the thickness of the oxide scale on the alloy containing Total Oxide Thickness Formed in Air at 2,000 F.
' v(inches) Base Alloy Elements Added (percent) (percent) Cr Mo s1 Al Ti Ca As MM 72 hrs.) (100 hrs.) 96 hrs.) 0.002 (100 hrs.) 0.010 (115 hrs.) 0.001 96 hrs.) 0.0007 (118 hrs.) 0.002 (100 hrs.) 0.0005 (118 hrs.) 0.005 (115 hrs.) 0.004 (115 hrs.)
Normally it would be expected that of these various alloys, those having the higher chromium contents would have lower melting points than the alloys in which the amounts of chromium and molybdenum are approximately equal. However, the minor constituents, such as silicon and aluminum, have very significant effects on melting temperature. For example, the alloy composed of 50.2% chromium, 48.8%.molybdenum, 0.5% silicon and 0.5% aluminum and the alloy containing 50% chromium, 47% molybdenum and 3% silicon were found to have melting points between 3200 F. and 3300 P. On the other hand, the alloy consisting of 68% chromium, 31.8%. molybdenum, 0.2% silicon and 0.03% aluminum melted between 3300 F. and 3400 F.
The refractory alloys described herein all were prepared by non-consumable arc-melting in an inert atmosphere of argon plus helium. Raw materials of maximum available purity were used. The constituents of the alloys may be added either simultaneously or successively.
Stress-rupture tests were conducted on as-cast chromium-molybdenum alloy test bars in an argon atmosphere at a temperature of 2000 F. under a load of 15,000 p.s.i. For example, an alloy consisting of about 48.2% chromium, 51.57% molybdenum, 0.18% silicon and 0.05% aluminum had a stress-rupture life of 37.8 hours under these conditions, On the other hand, 50 hours passed before a tensile test bar formed of an alloy comum, a small amount effective to materially increase the high-temperature oxidation resistance of said blade of at least one readily oxidizable member selected from the group consisting of silicon not in excess of 3%, aluminum not in excess of 0.5 titanium not in excess of 0.5%, calcium not in excess of 0.3%, arsenic not in excess of 0.08% and mischmetal not in excess of 0.15%, and'the balance substantially all molybdenum.
3. A chromium-molybdenum alloy having an oxide scale thickness of not in excess of about 0.005 inch after 100 hours exposure in air at a temperature of 2000 F., said alloy consisting essentially of about 45% to 70% chromium, 0.1% to 3% silicon and the balance substantially molybdenum.
4. An alloy characterized by high oxidation resistance at a temperature of 2000 F., said alloy consisting essentially of about 50% to 61% chromium, 39% to 50% molybdenum, silicon not in excess of 3%, and aluminum not in excess of 0.5%, the amount of silicon and aluminum present being sufficient to materially increase the oxidation resistance of said alloy at 2000 F.
5. An alloy having high oxidation resistance at elevated temperatures, said alloy consisting essentially of about 50% to 61% chromium, 39% to 50% molybdenum, silicon not in excess of 3%, aluminum not in excess of 0.5% and titanium not in excess of 0.5%, said a silicon, aluminum and titanium being present in amounts posed of approximately 62.4% chromium, 37.4% molybdenum, 0.17 %silicon and 0.03% aluminum was ruptured under the same test conditions.
While my invention has been described by means of certain specific examples, it is to be understood that the scope of my invention is not to be limited thereby except as defined in the following claims.
I claim:
1. An alloy consisting essentially of about 45% to 70% chromium, 30% to molybdenum, and a small amount effective to materially increase the high temperature oxidation resistance of said alloy of atleast one readily oxidizable member selected from the group consisting of silicon, aluminum, titanium, calcium, arsenic and mischmetal.
2. A gas turbine blade characterized by outstanding oxidation resistance upon exposure to oxidizing gases at a temperature of 2000 F., said blade being formed of an alloy consisting essentially of about 50% to 61% chromisufficient to materially increase the oxidation resistance of said alloy. at a temperature of 2000? F.
6. An oxidation-resistant alloy for use at extremely high temperatures, said alloy consisting essentially of 50% to 61% chromium, calcium not in excess of 0.3%, mischmetal not in excess of 0.15%, and the balance substantially molybdenum, said calcium and mischmetal being present in amounts suflicient to prevent the formation of an oxide scale on said alloy having an average thickness in excess of about 0.005 inch after hours exposure to air at a temperature of 2000 F.
7. An alloy characterized by high oxidation resistance at a temperature of 2000 F., said alloy consisting essentially of 50% to 61% chromium, 39% to 50% molybdenum, calcium not in excess of 0.3%, arsenic not in excess of 0.08%, and mischmetal not in excess of 0.15 said calcium, arsenic and mischmetal being present in amounts effective to prevent the oxide scale on said alloy from having an average thicknessin excess' of about 0.005 inch after 100 hours exposure to air at a temperature of 2000 F.
References Cited in the file of this patent UNITED STATES PATENTS 2,850,385 Nisbet Sept. 2, 1958 2,883,283 Wainer Apr. 21, 1959 2,955,937 McGurty et al Oct. 11, 1960 FOREIGN PATENTS.
517,155 Belgium May 15, 1956 787,097 Great Britain Dec. 4, 1957 OTHER REFERENCES Putman et al.: Transactions ASM, 1950 Preprint No. 26, pages 1 and 9 relied on. Published by the American Society for Metals, Cleveland, Ohio.
.Ductile Chromium, 1957, pages 233 and 236. Published by the American Society for Metals, Cleveland, Ohio.
Metals Handbook, Publ. by A.S.M., 1948 edition, p. 1194.

Claims (1)

1. AN ALLOY CONSISTING ESSENTIALLY OF ABOUT 45% TO 70% CHROMIUM, 30% TO 35% MOLYBDENUM, AND A SMALL AMOUNT EFFECTIVE TO MATERIALLY INCREASE THE HIGH TEMPERATURE OXIDATION RESISTANCE OF SAID ALLOY OF AT LEAST ONE READILY OXIDIZABLE MEMBER SELECTED FROM THE GROUP CONSISITING OF SILICON, ALUMINUM, TITANIUM, CALCIUM, ARSENIC AND MISCHMETAL.
US793935A 1959-02-17 1959-02-17 High temperature chromiummolybdenum alloy Expired - Lifetime US3030206A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US793935A US3030206A (en) 1959-02-17 1959-02-17 High temperature chromiummolybdenum alloy

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US793935A US3030206A (en) 1959-02-17 1959-02-17 High temperature chromiummolybdenum alloy

Publications (1)

Publication Number Publication Date
US3030206A true US3030206A (en) 1962-04-17

Family

ID=25161207

Family Applications (1)

Application Number Title Priority Date Filing Date
US793935A Expired - Lifetime US3030206A (en) 1959-02-17 1959-02-17 High temperature chromiummolybdenum alloy

Country Status (1)

Country Link
US (1) US3030206A (en)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3138456A (en) * 1956-10-22 1964-06-23 Commw Of Australia Chromium-tantalum alloys
US3174852A (en) * 1959-04-14 1965-03-23 Gen Motors Corp High temperature chromium-tungstenmolybdenum alloy
US3508910A (en) * 1966-02-01 1970-04-28 Crucible Inc Master alloy
WO2005118185A1 (en) * 2004-05-28 2005-12-15 Praxair S. T. Technology, Inc. Wear resistant alloy powders and coatings
RU2447175C1 (en) * 2010-11-26 2012-04-10 Государственное образовательное учреждение высшего профессионального образования Московский государственный вечерний металлургический институт Modifying agent for nickel alloys
RU2447177C1 (en) * 2010-11-26 2012-04-10 Государственное образовательное учреждение высшего профессионального образования Московский государственный вечерний металлургический институт Method of producing modifying agent for nickel alloys
RU2457270C1 (en) * 2010-11-26 2012-07-27 Государственное образовательное учреждение высшего профессионального образования Московский государственный вечерний металлургический институт Nickel alloy modifying method
RU2522926C1 (en) * 2013-04-09 2014-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Национальный исследовательский Томский государственный университет" Production of compacted iron modifier based on nano-dispersed powders
US9377245B2 (en) 2013-03-15 2016-06-28 Ut-Battelle, Llc Heat exchanger life extension via in-situ reconditioning
US9435011B2 (en) 2013-08-08 2016-09-06 Ut-Battelle, Llc Creep-resistant, cobalt-free alloys for high temperature, liquid-salt heat exchanger systems
US9540714B2 (en) 2013-03-15 2017-01-10 Ut-Battelle, Llc High strength alloys for high temperature service in liquid-salt cooled energy systems
US9605565B2 (en) 2014-06-18 2017-03-28 Ut-Battelle, Llc Low-cost Fe—Ni—Cr alloys for high temperature valve applications
US9683280B2 (en) 2014-01-10 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
US9683279B2 (en) 2014-05-15 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
RU2631545C1 (en) * 2016-04-20 2017-09-25 федеральное государственное бюджетное образовательное учреждение высшего образования "Нижегородский государственный технический университет им. Р.Е. Алексеева" (НГТУ) Modifying agent for heat-resistant nickel alloys
RU2632365C1 (en) * 2016-04-20 2017-10-04 федеральное государственное бюджетное образовательное учреждение высшего образования "Нижегородский государственный технический университет им. Р.Е. Алексеева" (НГТУ) Method of modifying heat-resistant nickel alloys
US10017842B2 (en) 2013-08-05 2018-07-10 Ut-Battelle, Llc Creep-resistant, cobalt-containing alloys for high temperature, liquid-salt heat exchanger systems
RU2706922C1 (en) * 2019-03-06 2019-11-21 федеральное государственное бюджетное образовательное учреждение высшего образования "Нижегородский государственный технический университет им. Р.Е. Алексеева" (НГТУ) Modifier for heat-resistant nickel-chromium alloys

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE517155A (en) *
GB787097A (en) * 1954-10-22 1957-12-04 Gen Electric Improvements in ductile chromium alloys
US2850385A (en) * 1955-08-29 1958-09-02 Universal Cyclops Steel Corp Molybdenum-base alloy
US2883283A (en) * 1957-07-02 1959-04-21 Horizons Inc Oxidation resistant molybdenum base alloy
US2955937A (en) * 1958-01-21 1960-10-11 James A Mcgurty Oxidation resistant chromium alloy

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE517155A (en) *
GB787097A (en) * 1954-10-22 1957-12-04 Gen Electric Improvements in ductile chromium alloys
US2850385A (en) * 1955-08-29 1958-09-02 Universal Cyclops Steel Corp Molybdenum-base alloy
US2883283A (en) * 1957-07-02 1959-04-21 Horizons Inc Oxidation resistant molybdenum base alloy
US2955937A (en) * 1958-01-21 1960-10-11 James A Mcgurty Oxidation resistant chromium alloy

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3138456A (en) * 1956-10-22 1964-06-23 Commw Of Australia Chromium-tantalum alloys
US3174852A (en) * 1959-04-14 1965-03-23 Gen Motors Corp High temperature chromium-tungstenmolybdenum alloy
US3508910A (en) * 1966-02-01 1970-04-28 Crucible Inc Master alloy
WO2005118185A1 (en) * 2004-05-28 2005-12-15 Praxair S. T. Technology, Inc. Wear resistant alloy powders and coatings
US20080274010A1 (en) * 2004-05-28 2008-11-06 Praxair Surface Technologies, Inc. Wear Resistant Alloy Powders and Coatings
RU2447175C1 (en) * 2010-11-26 2012-04-10 Государственное образовательное учреждение высшего профессионального образования Московский государственный вечерний металлургический институт Modifying agent for nickel alloys
RU2447177C1 (en) * 2010-11-26 2012-04-10 Государственное образовательное учреждение высшего профессионального образования Московский государственный вечерний металлургический институт Method of producing modifying agent for nickel alloys
RU2457270C1 (en) * 2010-11-26 2012-07-27 Государственное образовательное учреждение высшего профессионального образования Московский государственный вечерний металлургический институт Nickel alloy modifying method
US9377245B2 (en) 2013-03-15 2016-06-28 Ut-Battelle, Llc Heat exchanger life extension via in-situ reconditioning
US9540714B2 (en) 2013-03-15 2017-01-10 Ut-Battelle, Llc High strength alloys for high temperature service in liquid-salt cooled energy systems
RU2522926C1 (en) * 2013-04-09 2014-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Национальный исследовательский Томский государственный университет" Production of compacted iron modifier based on nano-dispersed powders
US10017842B2 (en) 2013-08-05 2018-07-10 Ut-Battelle, Llc Creep-resistant, cobalt-containing alloys for high temperature, liquid-salt heat exchanger systems
US9435011B2 (en) 2013-08-08 2016-09-06 Ut-Battelle, Llc Creep-resistant, cobalt-free alloys for high temperature, liquid-salt heat exchanger systems
US9683280B2 (en) 2014-01-10 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
US9683279B2 (en) 2014-05-15 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
US9752468B2 (en) 2014-06-18 2017-09-05 Ut-Battelle, Llc Low-cost, high-strength Fe—Ni—Cr alloys for high temperature exhaust valve applications
US9605565B2 (en) 2014-06-18 2017-03-28 Ut-Battelle, Llc Low-cost Fe—Ni—Cr alloys for high temperature valve applications
RU2631545C1 (en) * 2016-04-20 2017-09-25 федеральное государственное бюджетное образовательное учреждение высшего образования "Нижегородский государственный технический университет им. Р.Е. Алексеева" (НГТУ) Modifying agent for heat-resistant nickel alloys
RU2632365C1 (en) * 2016-04-20 2017-10-04 федеральное государственное бюджетное образовательное учреждение высшего образования "Нижегородский государственный технический университет им. Р.Е. Алексеева" (НГТУ) Method of modifying heat-resistant nickel alloys
RU2706922C1 (en) * 2019-03-06 2019-11-21 федеральное государственное бюджетное образовательное учреждение высшего образования "Нижегородский государственный технический университет им. Р.Е. Алексеева" (НГТУ) Modifier for heat-resistant nickel-chromium alloys

Similar Documents

Publication Publication Date Title
US3030206A (en) High temperature chromiummolybdenum alloy
US3164465A (en) Nickel-base alloys
US3061426A (en) Creep resistant alloy
US3366478A (en) Cobalt-base sheet alloy
JP2004307999A (en) Ni-BASED SUPER HEAT RESISTANT CAST ALLOY AND TURBINE WHEEL MADE THEREOF
US3723107A (en) Nickel-chromium-cobalt alloys for use at relatively high temperatures
US3293030A (en) Nickel-base alloys
US5167732A (en) Nickel aluminide base single crystal alloys
US2850385A (en) Molybdenum-base alloy
US3304176A (en) Nickel base alloy
JPH09165634A (en) Heat resistant titanium alloy
US3378368A (en) Titanium-base alloys
US3666453A (en) Titanium-base alloys
US4722828A (en) High-temperature fabricable nickel-iron aluminides
US3118763A (en) Cobalt base alloys
US5006308A (en) Nickel aluminide alloy for high temperature structural use
US2780545A (en) High-temperature alloy
US3046109A (en) High temperature niobium base alloy
US3022163A (en) Ductile niobium base alloy
US3069258A (en) Nickel-chromium casting alloy with niobides
US2981620A (en) Cobalt-nickel base alloy
US3597193A (en) Vanadium base alloy
US2575915A (en) Nickel base high-temperature alloy
US3065072A (en) Alloys with a nickel-chromium base
US3617397A (en) Cast nickel-base alloy