WO2018157228A1 - Superalliage soudable à base de nickel à teneur élevée en gamma prime et procédé de réparation et de fabrication de éléments de moteur à turbine utilisant ledit superalliage - Google Patents

Superalliage soudable à base de nickel à teneur élevée en gamma prime et procédé de réparation et de fabrication de éléments de moteur à turbine utilisant ledit superalliage Download PDF

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Publication number
WO2018157228A1
WO2018157228A1 PCT/CA2017/050291 CA2017050291W WO2018157228A1 WO 2018157228 A1 WO2018157228 A1 WO 2018157228A1 CA 2017050291 W CA2017050291 W CA 2017050291W WO 2018157228 A1 WO2018157228 A1 WO 2018157228A1
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per
hours
welding
temperature
manufacturing
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Alexander Goncharov
Joseph Liburdi
Paul Lowden
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Liburdi Engineering Ltd
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Liburdi Engineering Ltd
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Priority to PCT/CA2017/050291 priority Critical patent/WO2018157228A1/fr
Priority to CA3048051A priority patent/CA3048051C/fr
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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
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • 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
    • B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
    • B23K35/0222—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape for use in soldering or brazing
    • B23K35/0244—Powders, particles or spheres; Preforms made therefrom
    • 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
    • B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
    • B23K35/0255—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape for use in welding
    • B23K35/0261—Rods, electrodes or wires
    • 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°C
    • B23K35/3033—Ni as the principal constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • B22F2007/068—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts repairing articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/701—Heat treatment
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the high gamma prime nickel based superalloy which comprises 10 - 13 wt. % Co, 3 - 10 wt. % Cr, 0.5 - 2 wt. % Mo, 3 - 7 wt. % W, 0.5 - 10 wt. % Re, 5 - 6 wt. % Al, 5 - 7 wt. % Ta, 0.5 - 2 wt. % Hf, 0.01 - 0.15 wt. % C, 0.005 - 0.05 wt. B and 0.01 wt. % Zr, was first describe in the US Patent 4,169,742. Later on the optimized the optimized version of this alloy that comprises 12 wt.
  • Rene 142 or R142 superalloy that has been widely used as welding material and structural material for a manufacturing of directionally solidified (DS) turbine blades due to unique combination of oxidation resistance and high mechanical properties that were achieved by the optimization of Ta+Al+Cr content coupled with no titanium addition and high aluminum content combined with the special multi step heat treatment, refer to per Earl W. Ross and Kevin S. O'Hara, "Rene 142: A high strength, oxidation resistant DS turbine airfoil alloy", Superalloys 1982, pp. 257 - 265. The optimization of rupture properties of Rene 142 DS as per Earl W.
  • Si was not considered for a manufacturing of first, second and third generation of SX (single crystal) materials and high gamma prime superalloys due to its selective precipitation along grain boundaries that reduced mechanical properties of these material as shown in Table 1, refer to Tresa M. Pollock and Sammy Tin, "Nickel based superalloys for advanced turbine engines: Chemistry, Microstructure, and Properties", Journal of Propulsion and Power", Vol., 22, No. 2, March-April 2006, pp. 361 - 374.
  • % Sc+Y and micro alloying elements selected from among actinides and lanthanides. Inventors did not provide mechanical properties of this alloys. However, based on the lower content of gamma strengthening Al and elevated content of Cr, which alternated the ratio of Ta+Al+Cr from optimal, as it was established for Rene 142 superalloy, it is likely to assume that mechanical and oxidation properties of the superalloy described in EP Patent 2 100 982 were be below of properties of Rene 142 superalloy. Therefore, despite poor weldability, Rene 142 the best compromise for welding material for repair of turbine engine components.
  • Rene 142 superalloy is required to enhance weldability and mechanical properties of welds maintaining at the same time optimal ratio of Ta+Al+Cr.
  • the high gamma prime superalloy comprised of the 10 - 13 wt. % Co, 5 - 8 wt. % Cr, 1.0 - 2.5 wt. % Mo, 4 - 6 wt. % W, 6 - 7 wt. % Ta, 1.5 - 3.5 wt. % Re, 5.5 - 6.5 wt. % Al, 1.2 - 1.8 wt. % Hf, 0.01 - 0.02 wt. % B, 0.05 - 0.15 wt. % C with 0.15 - 0.25 wt.
  • Si is preferably in the form of refractory Ti, Ta and W silicide and disilicide, and preferably titanium disilicide (TiSi 2 ), further LWl superalloy, has good mechanical and oxidation properties, and better weldability than known Rene 142 superalloy.
  • the invented materials comprises the titanium and silicon with a ratio of 0.5 - 0.625 and preferably 0.5, when contents of titanium and solicon are in wt. % to allow preferential formation of Ti disilicide minimizing silicon content in a nickel based solid solution matrix and achieve combination of high oxidation resistance and mechanical properties at temperature > 1800°F.
  • the high gamma prime nickel based weldable material is selected from among welding wires and welding powder, equiaxed, directionally solidified and single crystal cast materials, extruded and cast articles, repair sections of turbine engine components and various materials and articles produced by 3D additive manufacturing process.
  • the method of repairing and manufacturing of turbine engine components includes the steps of pre-weld heat treatment of engine component using process parameters selected from among prescribed for the base material of engine component or the engine component manufactured of the same; pre-weld preparation of a base material by removal of a damaged material and contaminants to reveal a defect and contamination free base material; weld repair of a blade tip using a fusion welding process selected from among welding at an ambient temperature and preheating with the speed preferably from 1 to 3 inch per minute to enhance a formation of Ti-Ta-W silicide and disilicide, and preferably titanium disilicide, during welding, solidification and cooling of a welding pool, and a welding material comprising of 11 - 13 wt.
  • the post weld heat treatment comprises following below steps:
  • the post weld heat treatment comprises following below steps:
  • the preferable embodiment of the invented superalloy comprises the titanium and silicon with a ratio of 0.5 - 0.625 and preferably 0.50.
  • the tip of repaired blade is selected from among a squealer, tip cap or combination of above, wherein the squealer weld build up is performed after radial cracks repair.
  • the tip cap is manufactured by preferably an extrusion or 3D additive manufactured (further 3D AM) or casting and has equiaxed or directionally solidified orf single crystal structure followed by annealing and two steps aging.
  • extrusion or 3D additive manufactured further 3D AM
  • casting has equiaxed or directionally solidified orf single crystal structure followed by annealing and two steps aging.
  • Figure 1 is a typical HPT blade with the squealer tip design comprises: 100 - HPT blade, 101 - squealer and 102 - airfoil.
  • Figure 2 is a typical HPT blades that comprise 200 - airfoil, 201 - tip cap, 202 - squealer, 203 - weld of the tip cap to the airfoil depicting:
  • Blade tip with the combination of tip cap and squealer
  • Figure 3 depicts test weld samples after tensile testing at 1800°F with the test report on the background
  • Figure 4 is micrographs of LWl weld metal made with different magnifications depicting:
  • Figure 5 is mapping of alloying elements in the LWl weld metal wherein: a) Micrograph produced using ESM
  • Figure 6 is mapping of alloying elements in the LWl weld metal wherein: a) Distribution of Ti in the weld metal shown in Figure 5a.
  • Figure 7 is mapping of alloying elements in the LWl weld metal wherein: a) Distribution of W in the weld metal shown in Figure 5a. b) Distribution of Ni in the weld metal shown in Figure 5a that depicts a depletion of silicide with Ni.
  • Figure 8 is micrographs of Rene 142 welds that were additionally alloyed with Si depicting a formation of interdendritic silicide that reduced mechanical properties at high temperatures.
  • Figure 9 is the HPT blade manufactured of PWA1484 SX material after welding and heat treatment, wherein: a) HPT blades after PWHT
  • Equiaxed - having approximately equal dimensions in all directions; used especially of a crystal grain in metals and superalloys.
  • the invented superalloy can be used in the form of weld wire and powders for welding and plasma spray, equiaxed, DS and SX casting, various cast and extruded articles and repaired sections of turbine engine components.
  • welding materials in the form of welding wire and powder are major applications.
  • extruded LW1 is most advanced material for a manufacturing of tip caps for a repair of HPT blades shown in FIG.2.
  • welding and cladding are carried out with minimum dilution and heat input but at a low welding speed preferably of 1 - 3 inches per minute (ipm) aiming to increase the solidification time allowing a formation of complex refractory Ti-Ta-W based silicide and disilicide shown if Figures 5 -7 with melting temperatures from 2680 to 4000°F in the welding pool with the temperature of 2460 - 2500°F in lieu of a formation of various low temperature nickel silicide and disilicide (NiSi2) with melting temperature of 1819°F.
  • the invented method is disclosed by way of the example of the repair of turbine blades with the different tip design shown Figures 1 and 2 and examples of welding of samples manufactured of Mar M002 DS superalloy and repair of HPT turbine blade manufactured of PWA1484 SX superalloy using the invented LWl welding wire. These materials were selected for a demonstration due to high sensitivity to overheating, susceptibility to cracking and wide usage of these superalloy s for a manufacturing of HPT and LPT blades and vanes for industrial and aero turbine engines.
  • turbine blades Prior to the weld repair, turbine blades are subjected to stripping of the protective coatings followed by a pre-weld heat treatment prescribed by relevant OEM EM and SPM.
  • the type of a pre-weld heat treatment depends on the type of base materials. For example, only stress relief within the temperature range from 1800 to 2050°F can be used to prevent recrystallization of turbine blades manufactured of SX materials. Turbine blades
  • turbine blades are subjected to FPI as per AMS2647 and dimensional inspections followed by the tip grinding aiming to remove defective material and contaminants to reveal defects free base material.
  • HPT blades shown in Figure 1 in 'as welded' condition are subject to PWHT that depends of the type of the base material.
  • HPT blades manufactured of equiaxed and DS materials are subjected to annealing, for example for 2-4 hours at 2190-2230°F while HPT blades manufactured of SX material are subjected directly to a primary and secondary aging for 2-4 hours at 1975-2150 °F and for 16-24 hours at 1300-1400 °F respectively to exclude recrystallization of a base material.
  • HPT blades with the tip cap 201 and tip squealer 204 shown in Figure 2b or just tip cap 201 shown in Figure 2c prior to heat treatment are subjected to machining to restore the original geometry and installation of the tip cap 201 by a fusion, preferably GTAW or LBW, welding 203 followed by the selected as above PWHT.
  • a fusion preferably GTAW or LBW, welding 203 followed by the selected as above PWHT.
  • the tip cap can be manufactured by casting, 3D AM or extrusion and have equiaxed, DS or SX structure in a case of casting or equiaxed in case of using 3D AM and extrusion followed by PWHT.
  • the extrusion is most technological process for a manufacturing of materials with high TMF properties.
  • HPT blades are subjected to PWHT with parameters that depends on a type of a base material. It was found by experiments that to exclude
  • HPT blades should be subjected to PWHT that includes:
  • HPT blades manufactured of equiaxed and DS superalloys should be subjected to PWHT that includes: a) Annealing at a temperature of 2190 - 2230°F for 2 - 4 hours
  • EXAMPLE 1 Directionally solidified bars manufactured of Mar M002 superalloy were welded using GTAW-MA manual welding with LWl welding wire of 0.045 inch in diameter, weld current of 70 - 90 A and arc voltage 9 - 11 V at a room temperature with argon protection. Welding speed was varied within the range of 1-3 ipm to ensure a formation of the optimal microstructure constituting of precipitation of discrete refractory titanium, tantalum and tungsten silicide and disilicide in the gamma matrix.
  • Standard subsided samples were manufactured of welded bars as per ASTM E-8. Tensile tests were performed as per ASTM E-21 at a temperature of 1800°F. SRT was conducted as per ASTM E-139 at temperature of 1904°F and stresses of 18 KSI.
  • SEM Scanning Electron Microscope
  • EDS Energy Dispersive Spectroscopy

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Selon l'invention, le superalliage à base de nickel à teneur élevée en gamma prime, comprenant 10 à 13 % en poids de Co, 3 à 10 % en poids de Cr, 0,5 à 2 % en poids de Mo, 3 à 7% en poids de W, 0,5 à 10 % en poids de Re, 5 à 6 % en poids de Al, 5 à 7 % en poids de Ta, 0,5 à 2 % en poids de Hf, 0,01 à 0,15 % en poids de C, 0,005 à 0,05 % en poids de B et 0,01 % en poids de Zr, a d'abord été décrit dans le brevet américain 4 169 742. Ultérieurement, la version optimisée de cet alliage comprenant 12 % en poids de Co, 6,8 % en poids de Cr, 1,5 % en poids de Mo, 4,9 % en poids de W, 2,8 % en poids de Re, 6,15 % en poids de Al, 6,35 % en poids de Ta, 1,5 % en poids de Hf, 0,12 % en poids de C, 0,015 % en poids de B et 0,02 % en poids de Zr est devenue connue en tant que superalliage Rene 142 ou R142. Ce dernier a été largement utilisé en tant que matériau de soudage et matériau structural pour une fabrication de pales de turbine à solidification directionnelle (DS) en raison d'une association unique de résistance à l'oxydation et de propriétés mécaniques élevées, qui ont été obtenues par l'optimisation de la teneur en Ta + Al + Cr couplée à l'absence d'ajout de titane et à une teneur élevée en aluminium associée au traitement thermique en plusieurs étapes spécial, auquel font référence Earl W. Ross et Kevin S. O'Hara dans "Rene 142: A high strength, oxidation resistant DS turbine airfoil alloy", Superalloys 1982, pp. 257 - 265. L'optimisation des propriétés de rupture de Rene 142 DS selon Earl W. Ross et Kevin S. O'Hara a été obtenue par une homogénéisation à 2335 °F pendant 2 heures suivi par un recuit à 2050 °F pendant 4 heures, un vieillissement primaire à 1975 °F pendant 4 heures et un vieillissement secondaire à 1650 °F pendant 4 heures (désigné sous le nom de R142 HT).
PCT/CA2017/050291 2017-03-03 2017-03-03 Superalliage soudable à base de nickel à teneur élevée en gamma prime et procédé de réparation et de fabrication de éléments de moteur à turbine utilisant ledit superalliage Ceased WO2018157228A1 (fr)

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PCT/CA2017/050291 WO2018157228A1 (fr) 2017-03-03 2017-03-03 Superalliage soudable à base de nickel à teneur élevée en gamma prime et procédé de réparation et de fabrication de éléments de moteur à turbine utilisant ledit superalliage
CA3048051A CA3048051C (fr) 2017-03-03 2017-03-03 Superalliage soudable a base de nickel a teneur elevee en gamma prime et procede de reparation et de fabrication de elements de moteur a turbine utilisant ledit superalliage

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DE102018218017A1 (de) * 2018-10-22 2020-04-23 Siemens Aktiengesellschaft Reparatur einer Schaufelspitze mittels Coupon und Turbinenschaufel
CN113414519A (zh) * 2021-08-06 2021-09-21 四川大西洋焊接材料股份有限公司 交流用ENi6620镍基焊条及其制备方法与焊接方法
CN113814660A (zh) * 2021-09-23 2021-12-21 南通光明钼制品有限公司 一种金属钼端帽
CN114589429A (zh) * 2022-03-31 2022-06-07 广东省科学院中乌焊接研究所 一种用于叶轮增材修复的超级双相不锈钢药芯焊丝及其制备方法和应用
CN115488342A (zh) * 2022-08-31 2022-12-20 北京机电研究所有限公司 异种金属整体叶盘增等材短流程制备方法
CN117488110A (zh) * 2023-09-27 2024-02-02 中国航发沈阳黎明航空发动机有限责任公司 一种精密电解静子叶片用优质gh4169合金型材设计方法
US12123076B2 (en) 2019-01-16 2024-10-22 Safran Low density nickel-based superalloy having high mechanical strength and environmental robustness at a high temperatures
WO2025050686A1 (fr) * 2023-09-05 2025-03-13 东方电气集团东方汽轮机有限公司 Agent d'activation, pâte préfabriquée, élément préfabriqué et procédé de réparation de défauts de pénétration de paroi mince

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DE102018218017A1 (de) * 2018-10-22 2020-04-23 Siemens Aktiengesellschaft Reparatur einer Schaufelspitze mittels Coupon und Turbinenschaufel
CN109465570A (zh) * 2018-12-13 2019-03-15 郑州机械研究所有限公司 一种Ti-Si高温钎料
US12123076B2 (en) 2019-01-16 2024-10-22 Safran Low density nickel-based superalloy having high mechanical strength and environmental robustness at a high temperatures
CN113414519A (zh) * 2021-08-06 2021-09-21 四川大西洋焊接材料股份有限公司 交流用ENi6620镍基焊条及其制备方法与焊接方法
CN113414519B (zh) * 2021-08-06 2022-11-29 四川大西洋焊接材料股份有限公司 交流用ENi6620镍基焊条及其制备方法与焊接方法
CN113814660A (zh) * 2021-09-23 2021-12-21 南通光明钼制品有限公司 一种金属钼端帽
CN114589429A (zh) * 2022-03-31 2022-06-07 广东省科学院中乌焊接研究所 一种用于叶轮增材修复的超级双相不锈钢药芯焊丝及其制备方法和应用
CN114589429B (zh) * 2022-03-31 2022-08-30 广东省科学院中乌焊接研究所 一种用于叶轮增材修复的超级双相不锈钢药芯焊丝及其制备方法和应用
CN115488342A (zh) * 2022-08-31 2022-12-20 北京机电研究所有限公司 异种金属整体叶盘增等材短流程制备方法
CN115488342B (zh) * 2022-08-31 2024-04-02 中国机械总院集团北京机电研究所有限公司 异种金属整体叶盘增等材短流程制备方法
WO2025050686A1 (fr) * 2023-09-05 2025-03-13 东方电气集团东方汽轮机有限公司 Agent d'activation, pâte préfabriquée, élément préfabriqué et procédé de réparation de défauts de pénétration de paroi mince
CN117488110A (zh) * 2023-09-27 2024-02-02 中国航发沈阳黎明航空发动机有限责任公司 一种精密电解静子叶片用优质gh4169合金型材设计方法

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