US3918964A - Nickel-base alloys having a low coefficient of thermal expansion - Google Patents

Nickel-base alloys having a low coefficient of thermal expansion Download PDF

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US3918964A
US3918964A US427311A US42731173A US3918964A US 3918964 A US3918964 A US 3918964A US 427311 A US427311 A US 427311A US 42731173 A US42731173 A US 42731173A US 3918964 A US3918964 A US 3918964A
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alloy
alloys
thermal expansion
nickel
resistance
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US427311A
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English (en)
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James French Baldwin
Douglas H Maxwell
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Sorcery Metals Inc
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Sorcery Metals Inc
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Priority to US427311A priority Critical patent/US3918964A/en
Priority to GB50874A priority patent/GB1408372A/en
Priority to IL45853A priority patent/IL45853A/en
Priority to NO743817A priority patent/NO136104C/no
Priority to CA212,250A priority patent/CA1044921A/fr
Priority to IN2360/CAL/74A priority patent/IN140316B/en
Priority to FR7439356A priority patent/FR2255387B1/fr
Priority to DE2456857A priority patent/DE2456857C3/de
Priority to IT30646/74A priority patent/IT1027742B/it
Priority to SE7416036A priority patent/SE410620B/xx
Priority to BE151798A priority patent/BE823694A/fr
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Publication of US3918964A publication Critical patent/US3918964A/en
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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
    • C22C19/052—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 40%
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3033—Ni as the principal constituent
    • B23K35/304—Ni as the principal constituent with Cr as the next major constituent

Definitions

  • Alloy compositions consisting predominantly of 7 nickel, chromium. molybdenum. carbon. and boron [52] Cl 75/171; 75/134 F; 3 are disclosed.
  • the alloys possess a duplex structure consisting of a nickel-chromium-molybdenum matrix [51] C22C 19/05 and a semi-continuous network of refractory carbides [58] Field of Search 75/171 134 and borides.
  • a combination of desirable properties is 148/32 325 provided by these alloys. including elevated temperature strength. resistance to oxidation and hot corro- [56] Ei gs sion. and a very low coefficient of thermal expansion.
  • the present invention pertains to nickel base alloy compositions consisting predominantly of nickel, chin mium, molybdenum, and carbon. Preferably, the alloys also contain boron.
  • the alloys of the present invention provide a unique, and previously unavailable combination of properties including elevated temperature strength, resistance to oxidation, resistance to corrosion at elevated temperatures, and a very low coefiicient of thermal expansion.
  • the nickel base alloys of this invention are particularly useful for making hard facing welding rods both in cast wire and powder form; components for use in the glass forming industry; and components for use in hot sections of gas turbine engines, such as integral wheels, turbine shrouds, cases, seals, and the like.
  • Gas turbine engine shrouds may be visualized as an open ended, thin-walled cylinder.
  • a disk with radially attached blade air foils rotates about an axis which is common with the longitudinal axis of the cylinder.
  • the clearance between the tips of the rotating blades and the inside surface of the cylinder will to a large extent, control the efficiency of the engine. If the shroud expands more than the blade air foils during engine operation, the clearance increases and the engine efficiency falls off sharply.
  • Gas turbine engine components fabricated from alloys having low coefficients of thermal expansion are advantageous for reasons other than maintaining critical clearance dimensions. It has been determined that a low coefficient of thermal expansion is an essential physical property for improving thermal fatigue or thermal shock cycling resistance in high temperature alloys.
  • Alloys suitable for fabricating objects such as components for gas turbine engines desirably possess a number of other properties in addition to low coefficients of thermal expansion. Such alloys must simultaneously possess a number of high temperature properties including resistance to oxidation, sulfidation, and other forms of environmental deterioration.
  • exhaustive research has been conducted to develop alloys exhibiting resistance to oxidation and sulfidation. It is well recognized in the art that resistance to environmental deterioration in alloy compositions is controlled by the interaction of various alloying constituents. Chromium is by far the most influential solute element effecting resistance environmental deterioration. However, large amounts of chromium adversely affect high temperature creep rupture strength. For applications such as gas turbine components, high temperature creep rupture strength is also an important consideration.
  • the alloys currently used commercially for high temperature applications possess one, or in some instances two, of the three characteristics described heretofore (low coefficient of thermal expansion, high temperature corrosion resistance, and good creep rupture strength at elevated temperatures) that are desired in alloys useful for the fabrication of gas turbine components.
  • commercial nickel base alloys are available which exhibit remarkably low thermal expansion properties in comparison with typical high temperature alloys.
  • the very low chromium content of such alloys renders them unacceptable for use in the uncoated condition at temperatures over about l400F. in sulfidizing environments.
  • Such alloys deteriorate catastrophically at temperatures higher than 1,800F. under sulfidizing conditions.
  • Ni (Al Ti) an ordered intermetallic phase
  • the chromium content must be decreased in order to maintain an overall alloy composition that possesses microstructural stability and high temperature strength. As chromium content is decreased, the resistance to oxidation and sulfidization necessarily decreases.
  • compositions Despite the apparent dilemma of being able to select either a strong alloy or one with good resistance to environmental deterioration, a few compositions have evolved with a relatively good balance of both properties. However, even these compositions are suitable for use only in gas turbine engines employing high grade aviation fuels and operating conditions whereby hot corrosion and sulfidization are minimized, unless an oxidation and sulfidization resistant coating is applied to components formulated from such alloys.
  • Such alloys are not well suited for applications in which low thermal expansion is a primary concern.
  • Such alloys have high thermal expansion properties typical of nickel base superalloys.
  • Lobalt based superalloys rely on solid solution strengthening and a dispersion of primary carbides for elevated temperature strength. For this reason, cobalt based alloys will accommodate a significantly greater percentage of chromium than nickel base alloys. As a general proposition, cobalt base superalloys may be categorized as weaker, but more corrosion resistant, than nickel base materials. The expansion properties of cobalt base alloys are generally higher than nickel base alloys, making cobalt base alloys even less attractive for applications which require low thermal expansion.
  • the present invention pertains to nickel base alloy compositions possessing a very low coefficient of linear thermal expansion and sulfidation resistance adequate to enable use of uncoated components fabricated from the alloys in corrosive environments.
  • the alloys possess elevated temperature strength characteristics adequate to permit the alloys to be employed for numerous high temperature applications.
  • the alloys of the present invention contain unusually high levels of chromium and molybdenum.
  • chromium and molybdenum containing commercial nickel base alloys contain concentrations of chromium and molybdenum which are below the respective solubility limit of each element in nickel.
  • concentration of chromium and molybdenum far exceeds normal solubility limits in nickel.
  • the present invention provides a nickel-base alloy having a low coefficient of thermal expansion as well as elevated temperature strength and resistance to high temperature corrosion.
  • the present invention provides a nickel base alloy composition having a high elevated temperature hardness and corrosion resistance suitable for use in high temperature hard facing applications.
  • the present invention provides high strength nickel base alloys of sufficient chromium content to resist the fluxing action of molten oxides and thus is suitable for fabricating components useful in the manufacture of glass shapes.
  • the present invention pertains to nickel base alloy compositions consisting essentially of nickel, chromium, molybdenum, carbon and boron. These alloys have good elevated temperature strength, resistance to oxidation, and resistance to hot corrosion, as well as a very low coefficient of thermal expansion.
  • the invention also concerns components for use in gas turbine engines and hard facing welding rod made from such alloys.
  • Table I sets forth a broad range, an intermediate range, and two different and narrower ranges, in terms of percent by weight, of elements employed in the alloys of the present invention. It should be understood that the tabulation in Table I relates to each element individually, and is not intended to solely define composites of broad and narrow ranges. Nevertheless, composites of the narrower ranges specified in Table I represent particularly preferred embodiments.
  • the alloys of the present invention may contain minor amounts of other elements ordinarily included in nickel base alloys by those skilled in the art which will not substantially deleteriously affect the important characteristics of the alloy or which are inadvertently included in such alloys by virtue of impurity levels in commercial grades of alloying ingredients.
  • Impurities and incidental elements which may be present include titanium, manganese and silicon in amounts normally employed to achieve castability and melt deoxidation. Typically, these elements would be present in amounts less than l percent and preferably manganese and silicon would each be present in amounts of not more than 0.5 percent while titanium would be present in amounts of not more than 0.2 percent.
  • impurities and incidental elements which may be present in the alloys of the present invention include copper in amounts of not more than 0.5 percent, sulphur and phosphorous in amounts of not more than 0.20 percent and iron and cobalt in amounts of not more than 2.0 percent. Impurities such as nitrogen, hydrogen, tin, lead, bizmuth, calcium and magnesium should be held to as low a concentration as practical.
  • FIG. 1 is a graphical plot of thermal expansion properties of commercial iron, nickel and cobalt-base superalloys.
  • FIG. 2 is a graphical plot depicting hour creep rupture life for various commercial alloys.
  • FIG. 3 is a plot of thermal expansion properties for commercial iron, nickel and cobalt base superalloys and for example alloys of the present invention.
  • FIG. 4 is similar to FIG. 2 but represents example alloys of the present invention rather than commercial alloys.
  • high temperature alloys may possess some of the character istics desired in an alloy useful for fabricating components of gas turbine engines, but such alloys do not possess all of the desired characteristics. This may be illustrated with reference to several commercial alloys whose compositions are presented in Table II. As shown in FIG. 1, commercial alloys A and B of Table II show remarkably low thermal expansion properties in comparison with typical high temperature alloys. In FIG. 1, the shaded area designated 1 represents a range of mean coefficients of linear thermal expansion at various temperatures for 89 commercial iron, nickel and 6 forms stable carbides and both chromium and molybdenum form stable borides.
  • Curve 1 of FIG. 2 represents commercial alloy A. with the present invention containing both carbon and As may be further seen from FIG. 2, commercial alloy boron is 42,000 psi for rupture in I00 hours at l,500 C (curve 2) also lacks adequate elevated temperature F. This value is approximately 10 percent higher than strength. Commercial alloys D and E (curves 3 and 4, the strongest known cast cobalt-base superalloy. respectively, of FIG. 2) possess better high temperature A number of example alloy compositions in accorstrength characteristics, but not as high as desired at dance with the present invention were studied, using temperatures above about I,600F. Although the material melted and cast in air in standard shell test bar strength of commercial alloy B is excellent through and weld rod molds. Thirty to 50 lb. heats were produced for each composition studied. Response to heat about 2,200F., the total lack of environmental corrosion resistance severely restricts its use.
  • the amount of chromium available for brittle, acicular phase formation is reduced through the addition of carbon and boron.
  • Chromium treatment was determined by subjecting the test materials to a 24-hour aging exposure at 1,600 F. Alloys that demonstrated an aging response were given the l,600F. aging treatment prior to testing or were subjected to a 2,150F. stress relief/solution anneal prior to aging and testing.
  • Creep rupture tests were conducted at temperatures between 1,4.) 0F. and 2,000F. under loads that would enable comparison of properties with those of commercial alloys.
  • the measurements of thermal expansion properties were conducted on ground cylindrical specimens 2 inches in length and 0.200 inches in diameter using standard dialatometric methods.
  • Hot corrosion and resistance to sulfidization were studied by subjecting 1 inch long, 0.50 inch diameter, cylindrical specimens to a 300 hour partial exposure immersion in molten Na SO 10% NaCl salt mixture at 1,600F. Resistance was determined by the measurement of weight loss per unit area and by determination of surface recession rate by metallographic means.
  • FIG. 3 TABLE v commued in comparison with commerical alloys.
  • shaded area I represents the range of mean coefficient T ZQR- P Propeflies of linear thermal expansion over the temperature range Example a Life saucy-r100 Hr. between about 400F. and 1,600F. for 89 commercial 5 Alloy F, psi Hrs. 9 El. 9. Rupture Stress high temperature alloys while shaded area 2 represents RA the same range for 11 example alloys. As shown in FIG.
  • Table VI tabulates creep rupture test results for 1 13300 notched specimens. Time to rupture in hours at 13 I 30500 5 E 2 I,600F. under stress of 22,000 psi is given for a num- 1600 20.000 24.2 121 0 33.1 ber of example alloys. j: ii
  • FIG. 4 represents a plot of 100 hour creep rupture 2330 life as temperature versus stress for a number of exam- 14 1600 20.000 96.2 11.4 17.3 ple alloys.
  • 23 2 represent example alloys 4, 6 and 14. 5 5: 3 I
  • Example alloys 1 and 2 represent additions of relatively large percentages of carbon to ternary nickelchromium-molybdenum alloys that would show, absent the relatively large amount of carbon, microstructural instability. structurally, these alloys consist of primary metallic dendrites and primary herring bone" eutectic chromium-molybdenum carbides.
  • Example alloys 1 and 2 exhibited Rockwell hardness numbers C-scale, (Rc) of 33 and 42 respectively.
  • Example alloy 2 showed a slight softening to Re 38 upon aging. Rupture strength of both alloys is relatively low, but approaches that of cast cobalt-base superalloys.
  • Example alloy 4 not only has good strength, it possesses a lower mean coefficient of thermal expansion from 80F. to l,600F. than any other known nickelbase alloy.
  • the surprisingly low mean coefficient of thermal expansion of example alloy 4 from 80F to l,600F. is shown in Table IV. A comparison of this data with the curves of FIG. 1 illustrates the low degree of thermal expansion of example alloy 4 compared to various commercially available superalloys.
  • Example alloys 4 and 6, respectively, show a weight loss of 50.4 and 48.1 mg/cm and surface recession rates of 0.0035 and 0.002 inches in 300 hours in the sulfidization test. This represents excellent resistance to the severe test conditions employed and demonstrates that these alloys may be categorized as hot corrosion resistant.
  • example alloy 4 may be the more attractive material for certain types of use.
  • the very low expansivity combined with excellent hot corrosion resistance and moderate strength makes ex- 10 ample alloy 4 very attractive for fabricating components which require a very low degree of thermal expansion at elevated temperatures.
  • Compositional modifications around example alloys 4 and 6 resulted in some strength improvement over alloy 4, in example alloy 14, but at some sacrifice in expansion properties.
  • alloys of the present invention In producing the alloys of the present invention. and objects prepared from the alloys of the present invention, no special skills or techniques are required other than normal conventional foundry practice.
  • the alloys may be readily cast in sand, shell, or investment molds and melted and cast in air or under vacuum. Although the alloys were developed for use in the cast condition.
  • several specific compositions within the ambit of the present invention may be employed in wrought form if produced by powder metallurgy techniques.
  • the alloys of the present invention may generally be described as a class of nickel-base alloys possessing a duplex structure consisting of a nickel-chromiummolybdenum matrix and a semi-continuous network of refractory carbides and borides.
  • the alloy compositions possess a combination of physical and mechanical characteristics which have generally been considered mutually exclusive.
  • the balance of the alloy being essentially nickel and minor amounts of impurities and incidental elements which do not detrimentally affect the basic characteristics of the alloy, the carbon and boron being effective to prevent the formation of deleterious embrittling phases through formation of chromium and molybdenum borides and carbides.
  • the alloy of claim 1 which contains. on a weight basis, about 28 to about 42% chromium, and about 12 to about 20% molybdenum.
  • the alloy of claim 5 which contains, on a weight basis, about 16 to about 20 percent molybdenum and about 0.2% to about 0.7% boron.
  • a component for use in a gas turbine engine formed of the alloy of claim 5.
  • a component for use in a gas turbine engine formed of the alloy of claim 6.
  • a nickel base alloy having elevated temperature strength, resistance to oxidation and hot corrosion, and a low coefficient of thermal expansion consisting essentially of the following elements and the weight percentage ranges set forth:
  • the balance of the alloy being essentially nickel and minor amounts of impurties and incidental elements which do not detrimentally affect the basic characterish tics of the alloy, the carbon and boron being effective to prevent the formation of deleterious embrittling phases through formation of chromium and molybdenum borides and carbides.
  • a nickel base alloy having elevated temperature strength, resistance to oxidation and hot corrosion, and a low coefficient of thermal expansion consisting essentially of the following elements in the weight percentage ranges set forth:

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  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
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  • Organic Chemistry (AREA)
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  • Arc Welding In General (AREA)
US427311A 1973-12-21 1973-12-21 Nickel-base alloys having a low coefficient of thermal expansion Expired - Lifetime US3918964A (en)

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Application Number Priority Date Filing Date Title
US427311A US3918964A (en) 1973-12-21 1973-12-21 Nickel-base alloys having a low coefficient of thermal expansion
GB50874A GB1408372A (en) 1973-12-21 1974-01-04 Nickel base alloys
IL45853A IL45853A (en) 1973-12-21 1974-10-15 Nickel-base alloys having a low coefficient of thermal expansion
NO743817A NO136104C (no) 1973-12-21 1974-10-23 Nikkellegering med forh¦yet varmholdfasthet.
CA212,250A CA1044921A (fr) 1973-12-21 1974-10-25 Alliages a base de nickel a faible coefficient de dilation
IN2360/CAL/74A IN140316B (fr) 1973-12-21 1974-10-29
FR7439356A FR2255387B1 (fr) 1973-12-21 1974-12-02
DE2456857A DE2456857C3 (de) 1973-12-21 1974-12-02 Verwendung einer Nickelbasislegierung für unbeschichtete Bauteile im Heißgasteil von Turbinen
IT30646/74A IT1027742B (it) 1973-12-21 1974-12-17 Leghe a rase di nickel che pre sentano un basso coefficiente di dilatazione termica
SE7416036A SE410620B (sv) 1973-12-21 1974-12-19 Nickelbaserad legerign med lag vermeutvidgningskoefficient samt komponent och hardsvetselektrod av legeringen
BE151798A BE823694A (fr) 1973-12-21 1974-12-20 Alliages a base de nickel

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CA (1) CA1044921A (fr)
DE (1) DE2456857C3 (fr)
FR (1) FR2255387B1 (fr)
GB (1) GB1408372A (fr)
IL (1) IL45853A (fr)
IN (1) IN140316B (fr)
IT (1) IT1027742B (fr)
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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4207098A (en) * 1978-01-09 1980-06-10 The International Nickel Co., Inc. Nickel-base superalloys
US4363659A (en) * 1979-06-04 1982-12-14 Cabot Corporation Nickel-base alloy resistant to wear
US4374721A (en) * 1980-09-29 1983-02-22 Mitsubishi Steel Mfg. Co., Ltd. Roll having low volume resistivity for electroplating
US5424029A (en) * 1982-04-05 1995-06-13 Teledyne Industries, Inc. Corrosion resistant nickel base alloy
US6113849A (en) * 1997-07-18 2000-09-05 Ugine-Savoie Imphy S.A. Nickel-based alloy and welding electrode made of nickel-based alloy
US20050158203A1 (en) * 2002-01-08 2005-07-21 Katsuo Sugahara Nickel- based alloy with excellent corrosion resistance in inorganic-acid-containing supercritical water environment
WO2007023797A1 (fr) * 2005-08-25 2007-03-01 Solvothermal Crystal Growth Technology Research Alliance Alliage resistant a la corrosion a base de nickel et elements resistants a la corrosion fabriques a partir de cet alliage, pour appareil de reaction dans lequel est utilise de l'ammoniac supercritique
EP2853339A2 (fr) 2013-09-30 2015-04-01 Liburdi Engineering Limited Matériau de soudage pour le soudage de superalliages
EP3137253A4 (fr) * 2014-04-28 2017-10-04 Liburdi Engineering Limited Matériau de soudure à base de nickel comportant du bore ductile
US10352183B2 (en) * 2016-04-25 2019-07-16 United Technologies Corporation High temperature seal and method
CN110153590A (zh) * 2019-05-10 2019-08-23 中国铝业股份有限公司 一种Ni-Cr基合金焊丝及其制备方法
CN113172365A (zh) * 2021-05-08 2021-07-27 武汉科技大学 一种三元硼化物硬质合金堆焊焊条的制备方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4025314A (en) * 1975-12-17 1977-05-24 The International Nickel Company, Inc. Nickel-chromium filler metal
DE2837196A1 (de) * 1978-08-25 1980-03-06 Eaton Corp Legierung
ZA832119B (en) * 1982-04-05 1984-04-25 Teledyne Ind Corrosion resistant nickel base alloy

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1836317A (en) * 1928-10-31 1931-12-15 Electro Metallurg Co Corrosion resistant alloys
US2403128A (en) * 1942-06-24 1946-07-02 Westinghouse Electric Corp Heat resistant alloys
US3203792A (en) * 1961-04-01 1965-08-31 Basf Ag Highly corrosion resistant nickel-chromium-molybdenum alloy with improved resistance o intergranular corrosion

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1836317A (en) * 1928-10-31 1931-12-15 Electro Metallurg Co Corrosion resistant alloys
US2403128A (en) * 1942-06-24 1946-07-02 Westinghouse Electric Corp Heat resistant alloys
US3203792A (en) * 1961-04-01 1965-08-31 Basf Ag Highly corrosion resistant nickel-chromium-molybdenum alloy with improved resistance o intergranular corrosion

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4207098A (en) * 1978-01-09 1980-06-10 The International Nickel Co., Inc. Nickel-base superalloys
US4363659A (en) * 1979-06-04 1982-12-14 Cabot Corporation Nickel-base alloy resistant to wear
US4374721A (en) * 1980-09-29 1983-02-22 Mitsubishi Steel Mfg. Co., Ltd. Roll having low volume resistivity for electroplating
US5424029A (en) * 1982-04-05 1995-06-13 Teledyne Industries, Inc. Corrosion resistant nickel base alloy
US6113849A (en) * 1997-07-18 2000-09-05 Ugine-Savoie Imphy S.A. Nickel-based alloy and welding electrode made of nickel-based alloy
US7485199B2 (en) * 2002-01-08 2009-02-03 Mitsubishi Materials Corporation Ni based alloy with excellent corrosion resistance to supercritical water environments containing inorganic acids
US20050158203A1 (en) * 2002-01-08 2005-07-21 Katsuo Sugahara Nickel- based alloy with excellent corrosion resistance in inorganic-acid-containing supercritical water environment
US20090280024A1 (en) * 2005-08-25 2009-11-12 Solvolthermal Crystal Growth Technology Research Alliance Ni-based corrosion resistant alloy and corrosion resistant member for supercritical ammonia reactor made of the alloy
WO2007023797A1 (fr) * 2005-08-25 2007-03-01 Solvothermal Crystal Growth Technology Research Alliance Alliage resistant a la corrosion a base de nickel et elements resistants a la corrosion fabriques a partir de cet alliage, pour appareil de reaction dans lequel est utilise de l'ammoniac supercritique
US8414828B2 (en) 2005-08-25 2013-04-09 Furuya Metal Co., Ltd. Ni-based corrosion resistant alloy and corrosion resistant member for supercritical ammonia reactor made of the alloy
EP2853339A2 (fr) 2013-09-30 2015-04-01 Liburdi Engineering Limited Matériau de soudage pour le soudage de superalliages
EP2853339A3 (fr) * 2013-09-30 2015-08-12 Liburdi Engineering Limited Matériau de soudage pour le soudage de superalliages
EP3137253A4 (fr) * 2014-04-28 2017-10-04 Liburdi Engineering Limited Matériau de soudure à base de nickel comportant du bore ductile
US10352183B2 (en) * 2016-04-25 2019-07-16 United Technologies Corporation High temperature seal and method
CN110153590A (zh) * 2019-05-10 2019-08-23 中国铝业股份有限公司 一种Ni-Cr基合金焊丝及其制备方法
CN113172365A (zh) * 2021-05-08 2021-07-27 武汉科技大学 一种三元硼化物硬质合金堆焊焊条的制备方法
CN113172365B (zh) * 2021-05-08 2022-09-13 武汉科技大学 一种三元硼化物硬质合金堆焊焊条的制备方法

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Publication number Publication date
NO136104C (no) 1977-07-20
GB1408372A (en) 1975-10-01
BE823694A (fr) 1975-04-16
SE410620B (sv) 1979-10-22
DE2456857C3 (de) 1979-01-18
DE2456857A1 (de) 1975-07-03
IN140316B (fr) 1976-10-16
NO136104B (fr) 1977-04-12
DE2456857B2 (de) 1978-05-24
CA1044921A (fr) 1978-12-26
IL45853A0 (en) 1974-12-31
SE7416036L (fr) 1975-06-23
IL45853A (en) 1977-05-31
FR2255387A1 (fr) 1975-07-18
NO743817L (fr) 1975-07-21
IT1027742B (it) 1978-12-20
FR2255387B1 (fr) 1979-07-06

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