EP4359580B1 - Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine - Google Patents

Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine

Info

Publication number
EP4359580B1
EP4359580B1 EP22741349.9A EP22741349A EP4359580B1 EP 4359580 B1 EP4359580 B1 EP 4359580B1 EP 22741349 A EP22741349 A EP 22741349A EP 4359580 B1 EP4359580 B1 EP 4359580B1
Authority
EP
European Patent Office
Prior art keywords
superalloy
nickel
cex
superalloys
phase
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.)
Active
Application number
EP22741349.9A
Other languages
English (en)
French (fr)
Other versions
EP4359580A1 (de
Inventor
Jérémy RAME
Jonathan CORMIER
Lorena MATAVELI SUAVE
Edern MENOU
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.)
Safran Aircraft Engines SAS
Centre National de la Recherche Scientifique CNRS
Universite de Poitiers
Ecole National Superieure dArts et Metiers ENSAM
Safran SA
Original Assignee
Safran Aircraft Engines SAS
Centre National de la Recherche Scientifique CNRS
Universite de Poitiers
Ecole National Superieure dArts et Metiers ENSAM
Safran SA
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 Safran Aircraft Engines SAS, Centre National de la Recherche Scientifique CNRS, Universite de Poitiers, Ecole National Superieure dArts et Metiers ENSAM, Safran SA filed Critical Safran Aircraft Engines SAS
Publication of EP4359580A1 publication Critical patent/EP4359580A1/de
Application granted granted Critical
Publication of EP4359580B1 publication Critical patent/EP4359580B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • 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
    • C22C19/007—Alloys based on nickel or cobalt with a light metal (alkali metal Li, Na, K, Rb, Cs; earth alkali metal Be, Mg, Ca, Sr, Ba, Al Ga, Ge, Ti) or B, Si, Zr, Hf, Sc, Y, lanthanides, actinides, as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/606—Directionally-solidified crystalline structures
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • This presentation concerns nickel-based superalloys for gas turbines, in particular for the fixed blades, also called distributors or rectifiers, or mobile blades of a gas turbine, for example in the field of aeronautics.
  • nickel-based superalloys for single-crystal blades have undergone significant changes in chemical composition, particularly with the aim of improving their high-temperature creep properties while maintaining resistance to the highly aggressive environment in which these superalloys are used.
  • metallic coatings suitable for these alloys have been developed to increase their resistance to the aggressive environment in which these alloys are used, including oxidation resistance and corrosion resistance.
  • a low thermal conductivity ceramic coating which acts as a thermal barrier, can be added to reduce the temperature at the metal surface.
  • M Ni (nickel) or Co (cobalt)
  • Cr chromium
  • NiAlyPtz nickel aluminide type alloys
  • the second layer is a ceramic coating comprising, for example, yttria-containing zirconia, also referred to as “YSZ” or “YPSZ” and having a porous structure.
  • This layer can be deposited by various processes, such as electron beam evaporation (“EB-PVD” or “Electron Beam Physical Vapor Deposition”), thermal spraying (“APS” or “SPS” or “Suspension Plasma Spraying”), or any other process that provides a porous ceramic coating with low thermal conductivity.
  • inter-diffusion phenomena occur at the microscopic scale between the nickel-based superalloy of the substrate and the metallic alloy of the underlayer.
  • These inter-diffusion phenomena associated with the oxidation of the underlayer, modify in particular the chemical composition, the microstructure and consequently the mechanical properties of the underlayer from the manufacturing of the coating, then during the use of the blade in the turbine.
  • These inter-diffusion phenomena also modify the chemical composition, the microstructure and consequently the mechanical properties of the superalloy of the substrate under the coating.
  • SRZ secondary reaction zone
  • casting defects are likely to form in parts, such as blades, during their manufacture by directional solidification. These defects are generally parasitic grains of the “Freckle” type, the presence of which can cause premature failure of the part in service. The presence of these defects, linked to the chemical composition of the superalloy, generally leads to the rejection of the part, which results in an increase in the production cost.
  • FR 3 081 883 A1 discloses nickel-based superalloys for gas turbines.
  • This presentation aims to propose nickel-based superalloy compositions for the manufacture of single-crystal components, presenting increased performance in terms of service life and mechanical resistance and making it possible to reduce the production costs of the part (reduction of the scrap rate) compared to existing alloys.
  • These superalloys exhibit higher high-temperature creep strength than existing alloys while demonstrating good microstructural stability in the volume of the superalloy (low sensitivity to PTC formation), good microstructural stability under the thermal barrier coating sub-layer (low sensitivity to ZRS formation), good resistance to oxidation and corrosion while avoiding the formation of parasitic grains of the “Freckle” type.
  • the present disclosure relates to a nickel-based superalloy as defined in claim 1 in the appendix.
  • This superalloy is intended for the manufacture of single-crystal gas turbine components, such as fixed or moving blades.
  • This alloy therefore has improved high-temperature creep resistance. As the alloy has a long service life, it also has improved corrosion and oxidation resistance. This alloy can also have improved thermal fatigue resistance.
  • These superalloys have a density greater than or equal to 8.75 g/cm 3 and less than or equal to 8.95 g/cm 3 (gram per cubic centimeter).
  • a single-crystal nickel-based superalloy part is obtained by a directed solidification process under thermal gradient in a lost-wax casting process.
  • the single-crystal nickel-based superalloy comprises an austenitic matrix of face-centered cubic structure, a nickel-based solid solution, called gamma phase (" ⁇ ").
  • This matrix contains precipitates of gamma prime hardening phase (“ ⁇ '”) of ordered cubic structure L1 2 of type Ni 3 Al. The whole (matrix and precipitates) is therefore described as a ⁇ / ⁇ ' superalloy.
  • this composition of the nickel-based superalloy allows the implementation of a heat treatment which redissolves the ⁇ ' phase precipitates and the ⁇ / ⁇ ' eutectic phases which form during the solidification of the superalloy. It is thus possible to obtain a single-crystal nickel-based superalloy containing ⁇ ' precipitates of controlled size, preferably between 300 and 500 nanometers (nm), and containing a small proportion of ⁇ / ⁇ ' eutectic phases.
  • Heat treatment also allows the mole fraction of ⁇ ' phase precipitates present in the nickel-based monocrystalline superalloy to be controlled.
  • the mole percentage of ⁇ ' phase precipitates may be greater than or equal to 50%, preferably greater than or equal to 60%, even more preferably equal to 70%.
  • the major addition elements are cobalt (Co), chromium (Cr), molybdenum (Mo), rhenium (Re), tungsten (W), aluminum (Al), tantalum (Ta) and platinum (Pt).
  • Co cobalt
  • Cr chromium
  • Mo molybdenum
  • Re rhenium
  • W tungsten
  • Al aluminum
  • Ta tantalum
  • Pt platinum
  • the minor addition elements are hafnium (Hf) and silicon (Si), for which the maximum mass content is less than 1% by mass.
  • unavoidable impurities examples include sulfur (S), carbon (C), boron (B), yttrium (Y), lanthanum (La), and cerium (Ce).
  • Unavoidable impurities are defined as elements that are not intentionally added to the composition and are introduced with other elements.
  • the superalloy may contain 0.005% carbon by mass.
  • tungsten, chromium, cobalt, rhenium or molybdenum mainly serves to strengthen the ⁇ austenitic matrix of face-centered cubic (FCC) crystal structure by solid solution hardening.
  • the simultaneous addition of silicon and hafnium improves the hot oxidation resistance of nickel-based superalloys by increasing the adhesion of the alumina layer (Al 2 O 3 ) that forms on the surface of the superalloy at high temperature.
  • This alumina layer forms a passivation layer on the surface of the nickel-based superalloy and a barrier to the diffusion of oxygen from the outside to the inside of the nickel-based superalloy.
  • hafnium can be added without also adding silicon or conversely silicon can be added without also adding hafnium and still improve the hot oxidation resistance of the superalloy.
  • chromium or aluminum can improve the oxidation and high-temperature corrosion resistance of the superalloy.
  • chromium is essential for increasing the hot corrosion resistance of nickel-based superalloys.
  • too high a chromium content tends to reduce the solvus temperature of the ⁇ ' phase of the nickel-based superalloy, i.e., the temperature above which the ⁇ ' phase is completely dissolved in the ⁇ matrix, which is undesirable.
  • the chromium concentration is between 5.0 and 7.5% in mass in order to maintain a high solvus temperature of the ⁇ ' phase of the nickel-based superalloy, for example greater than or equal to 1300°C but also to avoid the formation of topologically compact phases in the ⁇ matrix highly saturated with alloying elements such as rhenium, molybdenum or tungsten.
  • cobalt which is an element close to nickel and partially substitutes for nickel, forms a solid solution with nickel in the ⁇ matrix.
  • Cobalt helps strengthen the ⁇ matrix, reduce the sensitivity to PTC precipitation and ZRS formation in the superalloy under the protective coating.
  • too high a cobalt content tends to reduce the solvus temperature of the ⁇ ' phase of the nickel-based superalloy, which is undesirable.
  • the chromium and cobalt content is optimized to obtain adequate solvus temperatures with the intended applications both for the desired mechanical properties and for the heat treatment capacity of the superalloy with a heat treatment window compatible with industrial needs, i.e. a difference between the solvus temperature and the solidus temperature of the superalloy that is sufficiently wide.
  • the addition of platinum increases the temperature stability of the ⁇ ' phase by maintaining the fraction of hardening ⁇ ' phase precipitates high compared to common alloys where this fraction decreases significantly during temperature increase. This maintenance of a high proportion of ⁇ ' precipitates at high temperature allows the mechanical properties of the alloy to be maintained at temperatures close to the ⁇ ' solvus temperature of the alloy.
  • the addition of platinum improves the oxidation and corrosion resistance of the superalloy. Adding platinum to the superalloy thus improves the service life of the system comprising a superalloy covered with a metallic coating and a thermal barrier.
  • the addition of platinum to the chemical composition of the superalloy makes it possible to reduce, or eliminate, the addition of platinum in the coating.
  • refractory elements such as molybdenum, tungsten, rhenium or tantalum, helps to slow down the mechanisms controlling the creep of nickel-based superalloys and which depend on the diffusion of chemical elements in the superalloy.
  • a very low sulfur content in a nickel-based superalloy increases the resistance to oxidation and hot corrosion, as well as the resistance to spalling of the thermal barrier.
  • a low sulfur content less than 2 ppm by mass (parts per million by mass), or ideally less than 0.5 ppm by mass, optimizes these properties.
  • Such a mass sulfur content can be achieved by producing a low-sulfur master casting or by a desulfurization process carried out after casting. In particular, it is possible to maintain a low sulfur level by adapting the superalloy production process.
  • Nickel-based superalloys are superalloys whose mass percentage is predominantly nickel. It is understood that nickel is therefore the element whose mass percentage in the alloy is the highest.
  • the superalloy comprises, in mass percentages, 5.4 to 6.0% of aluminum, 7.5 to 8.5% of tantalum, 2.0 to 4.0% of cobalt, 5.0 to 7.5% of chromium, 0 to 0.20% of molybdenum, 4.5 to 6.0% of tungsten, 1.50 to 3.5% of rhenium, 1.0 to 4.0% of platinum, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder being nickel and unavoidable impurities.
  • the superalloy may comprise, in mass percentages, 5.6 to 6.0% of aluminum, 7.5 to 8.5% of tantalum, 2.0 to 4.0% of cobalt, 6.5 to 7.5% of chromium, 4.5 to 5.5% of tungsten, 1.50 to 2.25% of rhenium, 1.5 to 2.5% of platinum, 0.05 to 0.15% of hafnium, 0 to 0.15% of silicon, the remainder being nickel and unavoidable impurities.
  • the superalloy may comprise, in mass percentages, 5.8% aluminum, 8.0% tantalum, 3.0% cobalt, 7.0% chromium, 5.0% tungsten, 1.75% rhenium, 2.0% platinum, 0.05% hafnium, the remainder being nickel and unavoidable impurities.
  • the superalloy may comprise, in mass percentages, 5.6% aluminum, 8.0% tantalum, 3.0% cobalt, 6.0% chromium, 0.20% molybdenum, 5.5% tungsten, 3.0% rhenium, 2.0% platinum, 0.05% hafnium, the remainder being nickel and unavoidable impurities.
  • This disclosure also relates to a single-crystal blade for a turbomachine comprising a superalloy as defined previously.
  • This blade therefore has improved high temperature creep resistance. This blade therefore has improved oxidation and corrosion resistance.
  • the blade may include a protective coating comprising a metallic undercoat deposited over the superalloy and a ceramic thermal barrier deposited over the metallic undercoat.
  • the composition of the nickel-based superalloy Due to the composition of the nickel-based superalloy, the formation of a secondary reaction zone in the superalloy resulting from inter-diffusion phenomena between the superalloy and the sub-layer is avoided, or limited.
  • the metallic underlayer may be an MCrAlY type alloy or a nickel aluminide type alloy.
  • the ceramic thermal barrier may be a yttria-based zirconia material or any other low thermal conductivity ceramic (zirconia-based) coating.
  • the blade may have a structure oriented along a crystallographic direction ⁇ 001>.
  • This orientation generally gives the blade the optimal mechanical properties.
  • This disclosure also relates to a turbomachine comprising a blade as defined previously.
  • FIG. 1 is a schematic longitudinal sectional view of a turbomachine.
  • Nickel-based superalloys are intended for the manufacture of single-crystal blades by a directed solidification process in a thermal gradient.
  • the use of a single-crystal seed or a grain selector at the beginning of solidification makes it possible to obtain this single-crystal structure.
  • the structure is oriented, for example, along a crystallographic direction ⁇ 001>, which is the orientation that generally gives the optimal mechanical properties to superalloys.
  • As-solidified single-crystal nickel-based superalloys have a dendritic structure and consist of ⁇ ' Ni 3 (Al, Ti, Ta) precipitates dispersed in a ⁇ matrix of face-centered cubic structure, a nickel-based solid solution. These ⁇ ' phase precipitates are heterogeneously distributed in the volume of the single crystal due to chemical segregations resulting from the solidification process. Furthermore, ⁇ / ⁇ ' eutectic phases are present in the inter-dendritic regions and constitute preferential sites for crack initiation. These ⁇ / ⁇ ' eutectic phases form at the end of solidification.
  • the ⁇ / ⁇ ' eutectic phases are formed at the expense of fine precipitates (sub-micrometer size) of the hardening ⁇ ' phase. These ⁇ ' phase precipitates constitute the main source of hardening of nickel-based superalloys. Also, the presence of residual ⁇ / ⁇ ' eutectic phases does not allow the hot creep resistance of the nickel-based superalloy to be optimized.
  • the first heat treatment is a microstructure homogenization treatment which aims to dissolve the ⁇ ' phase precipitates and eliminate the ⁇ / ⁇ ' eutectic phases or significantly reduce their molar fraction.
  • This treatment is carried out at a temperature above the solvus temperature of the ⁇ ' phase and below the incipient melting temperature of the superalloy (T solidus ). Quenching is then carried out at the end of this first heat treatment to obtain a fine and homogeneous dispersion of the ⁇ ' precipitates.
  • Tempering heat treatments are then carried out in two stages, at temperatures below the solvus temperature of the ⁇ ' phase. In a first step, to increase the ⁇ ' precipitates and obtain the desired size, then in a second step, to increase the molar fraction of this phase up to approximately 70% at room temperature.
  • FIG. 1 represents, in section along a vertical plane passing through its main axis A, a double-flow turbojet 10.
  • the double-flow turbojet 10 comprises, from upstream to downstream according to the circulation of the air flow, a fan 12, a low-pressure compressor 14, a high-pressure compressor 16, a combustion chamber 18, a high-pressure turbine 20, and a low-pressure turbine 22.
  • the high-pressure turbine 20 comprises a plurality of moving blades 20A rotating with the rotor and rectifiers 20B (fixed blades) mounted on the stator.
  • the stator of the turbine 20 comprises a plurality of stator rings 24 arranged opposite the moving blades 20A of the turbine 20.
  • a moving blade 20A or a rectifier 20B for a turbomachine comprising a superalloy as defined previously coated with a protective coating including a metallic undercoat
  • Example 1 and Ex 2 Two nickel-based single-crystal superalloys from this paper (Ex 1 and Ex 2) were studied and compared with five commercial single-crystal superalloys (reference alloys) and two experimental single-crystal superalloys CEx 6 and CEx 7.
  • the experimental single-crystal superalloy CEx 6 is cited in the publication JS Van Sluytman, CJ Moceri, and TM Pollock, “A Pt-modified Ni-base superalloy with high temperature precipitate stability,” Mater. Sci. Eng. A, vol. 639, p. 747-754, Jul.
  • each of the single-crystal superalloys is given in Table 1, with compositions CEx 1 and CEx 4 further comprising 0.05% by mass of carbon (C) and 0.004% by mass of boron (B), and composition CEx 6 further comprising 0.02% by mass of carbon, 0.015% by mass of boron and 0.02% by mass of zircon. All these superalloys are nickel-based superalloys, i.e. the remainder of the compositions presented to 100% is nickel and unavoidable impurities.
  • the room temperature density of each superalloy was estimated using a modified version of Hull's formula ( FC Hull, Metal Progress, November 1969, pp139-140 ). This empirical equation was proposed by Hull. The empirical equation is based on the law of mixtures and includes correction terms deduced from a linear regression analysis of experimental data (chemical compositions and measured densities) for 235 superalloys and stainless steels.
  • the calculated densities for the alloys of the invention are greater than or equal to 8.75 g/cm 3 and less than or equal to 8.95 g/cm 3 (see Table 2).
  • Density is of prime importance for rotating component applications such as turbine blades. Indeed, an increase in the density of the superalloy of the blades requires reinforcement of the disc carrying them, and therefore another additional weight cost. It can be seen that the Ex 1 and Ex 2 superalloys have similar densities to the comparison superalloys, with the exception of the CEx4 superalloy which has a higher density.
  • This equation (2) was obtained by multiple linear regression analysis from observations made after aging for 400 hours at 1093°C (degree centigrade) of samples of various nickel-based superalloys of the René N6 ® alloy family under a NiPtAl coating.
  • NFP % Ta + 1 , 5 % Hf + 0 , 5 % Mo ⁇ 0 , 5 %% Ti / % W + 1 , 2 % Re
  • %Cr, %Ni, ...%X are the contents, expressed as mass percentages, of the elements of the superalloy Cr, Ni, ..., X.
  • the NFP parameter allows to quantify the sensitivity to the formation of parasitic grains of the “Freckles” type during the directional solidification of the part (document US 5,888,451 ). To avoid the formation of “Freckles” type defects, the NFP parameter must be greater than or equal to 0.7. Low sensitivity to this type of defect is an important parameter because it implies a low reject rate linked to this defect during the manufacture of parts.
  • superalloys Ex 1 to Ex 2 have an NFP parameter greater than or equal to 0.7.
  • Commercial superalloys such as CEx 2 to CEx 5 have higher sensitivities to the formation of this type of defects as shown in Table 2.
  • a low Sensitivity to this type of defect is an important parameter because it implies a low rate of rejection linked to this defect during the manufacture of parts.
  • Table 2 shows different parameters for superalloys Ex 1 and Ex 2 and CEx 1 to CEx 7.
  • Density (1) (g/cm 3 ) [ZRS(%)] 1/2 NFP Cost ($/kg) Ex 1 8.76 -32 1.10 579 Ex 2 8.89 -18 0.90 612 CEx 1 8.61 -22 0.85 136 CEx 2 8.76 -14 0.67 140 CEx 3 8.95 4 0.68 184 CEx 4 9.92 1 0.69 199 CEx 5 8.96 16 0.67 206 CEx 6 8.92 -16 1.05 2008
  • the CALPHAD method was used to calculate the solidus temperatures of superalloys Ex 1, Ex 2 and CEx 1 to CEx 7.
  • TTH Heat Treatment Interval
  • ThermoCalc software (TCNI9 database) based on the CALPHAD method was used to calculate the heat treatment interval of superalloys.
  • the manufacturability of the alloys of the invention was also estimated from the possibility of industrially resolving the ⁇ ' phase precipitates to optimize the mechanical properties of the alloys.
  • the heat treatment interval was estimated from the calculation of the solidus temperature and the solvus temperature of the ⁇ ' phase precipitates of the alloys.
  • the Ex 1 and Ex 2 superalloys have wide heat treatment windows, of the order of 20°C and more, which is compatible with industrial furnaces. It is noted that the reference superalloys comprising CEx 6 or CEx 7 platinum have more restricted heat treatment intervals and are therefore less easily heat treatable without risk of burning the alloy, taking into account the uncertainty of industrial furnaces at these temperatures which can be +/- 10°C.
  • the CALPHAD method was used to calculate the mole fraction (in mole percentage) of ⁇ ' phase at equilibrium in superalloys Ex 1, Ex 2 and CEx 1 to CEx 7 at 750°C, 1100°C and 1250°C.
  • superalloys Ex 1 and Ex 2 contain particularly high molar fractions of ⁇ ' phase at very high temperature (1250°C) (30%), which ensures strong mechanical strength of the alloy at these extreme temperatures.
  • superalloys Ex 1 and Ex 2 have mole fractions of ⁇ ' precipitate twice as high as those of the reference alloy CEx 7 and a ⁇ ' solvus more than 40°C higher, which implies an increased heat resistance of these superalloys compared to the reference superalloy CEx 7.
  • the example alloys of the invention thus present a strong potential for high temperature applications, in particular for the manufacture of turbine blades, combining an adequate compromise combining low density, high mechanical strength, low sensitivity to the formation of defects (PTC, ZRS, casting defects), while retaining high resistance to oxidation and corrosion.

Landscapes

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

Claims (8)

  1. Superlegierung auf Nickelbasis, umfassend in Massenprozent 5,4 bis 6,0 % Aluminium, 7,5 bis 8,5 % Tantal, 2,0 bis 4,0 % Kobalt, 5,0 bis 7,5 % Chrom, 0 bis 0,20 % Molybdän, 4,5 bis 6,0 % Wolfram, 1,50 bis 3,5 % Rhenium, 1,0 bis 4,0 % Platin, 0,05 bis 0,25 % Hafnium, 0 bis 0,15 % Silizium, wobei der Rest aus Nickel und unvermeidbaren Verunreinigungen besteht.
  2. Superlegierung nach Anspruch 1, umfassend in Massenprozent 5,6 bis 6,0 % Aluminium, 7,5 bis 8,5 % Tantal, 2,0 bis 4,0 % Kobalt, 6,5 bis 7,5 % Chrom, 4,5 bis 5,5 % Wolfram, 1,50 bis 2,25 % Rhenium, 1,5 bis 2,5 % Platin, 0,05 bis 0,15 % Hafnium, 0 bis 0,15 % Silizium, wobei der Rest aus Nickel und unvermeidbaren Verunreinigungen besteht.
  3. Superlegierung nach Anspruch 1, umfassend in Massenprozent 5,8 % Aluminium, 8,0 % Tantal, 3,0 % Kobalt, 7,0 % Chrom, 5,0 % Wolfram, 1,75 % Rhenium, 2,0 % Platin, 0,05 % Hafnium, wobei der Rest aus Nickel und unvermeidbaren Verunreinigungen besteht.
  4. Superlegierung nach Anspruch 1, umfassend in Massenprozent 5,6 % Aluminium, 8,0 % Tantal, 3,0 % Kobalt, 6,0 % Chrom, 0,20 % Molybdän, 5,5 % Wolfram, 3,0 % Rhenium, 2,0 % Platin, 0,05 % Hafnium, wobei der Rest aus Nickel und unvermeidbaren Verunreinigungen besteht.
  5. Monokristalline Schaufel (20A, 20B) für eine Turbomaschine, die eine Superlegierung nach einem der Ansprüche 1 bis 4 umfasst.
  6. Schaufel (20A, 20B) nach Anspruch 5, die eine Schutzbeschichtung umfasst, die eine auf die Superlegierung aufgebrachte Metallunterschicht und eine auf die Metallunterschicht aufgebrachte keramische Wärmesperre umfasst.
  7. Schaufel (20A, 20B) nach Anspruch 5 oder 6, die eine in einer kristallographischen Richtung <001 > ausgerichtete Struktur aufweist.
  8. Turbomaschine, die eine Schaufel (20A, 20B) nach einem der Ansprüche 5 bis 7 umfasst.
EP22741349.9A 2021-06-22 2022-06-17 Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine Active EP4359580B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2106613A FR3124194B1 (fr) 2021-06-22 2021-06-22 Superalliage a base de nickel, aube monocristalline et turbomachine
PCT/FR2022/051185 WO2022269177A1 (fr) 2021-06-22 2022-06-17 Superalliage a base de nickel, aube monocristalline et turbomachine

Publications (2)

Publication Number Publication Date
EP4359580A1 EP4359580A1 (de) 2024-05-01
EP4359580B1 true EP4359580B1 (de) 2025-10-08

Family

ID=78827702

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22741349.9A Active EP4359580B1 (de) 2021-06-22 2022-06-17 Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine

Country Status (5)

Country Link
US (1) US20240287650A1 (de)
EP (1) EP4359580B1 (de)
CN (1) CN117677721A (de)
FR (1) FR3124194B1 (de)
WO (1) WO2022269177A1 (de)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5270123A (en) 1992-03-05 1993-12-14 General Electric Company Nickel-base superalloy and article with high temperature strength and improved stability
DE19624055A1 (de) 1996-06-17 1997-12-18 Abb Research Ltd Nickel-Basis-Superlegierung
US8449262B2 (en) * 2009-12-08 2013-05-28 Honeywell International Inc. Nickel-based superalloys, turbine blades, and methods of improving or repairing turbine engine components
FR3081883B1 (fr) * 2018-06-04 2020-08-21 Safran Superalliage a base de nickel, aube monocristalline et turbomachine

Also Published As

Publication number Publication date
CN117677721A (zh) 2024-03-08
FR3124194A1 (fr) 2022-12-23
EP4359580A1 (de) 2024-05-01
US20240287650A1 (en) 2024-08-29
WO2022269177A1 (fr) 2022-12-29
FR3124194B1 (fr) 2023-11-24

Similar Documents

Publication Publication Date Title
EP3532648B1 (de) Superlegierung auf der basis von nickel, einkristalline turbinenschaufel und strömungsmaschine
EP3710610B1 (de) Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine
EP3710611B1 (de) Superlegierung auf nickelbasis, einkristallschaufel und turbomaschine
EP3802895B1 (de) Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine
EP4367278B1 (de) Superlegierung auf nickelbasis, einkristalline leitschaufel und turbinenmotor
EP4359580B1 (de) Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine
EP4314370A1 (de) Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine
EP4581183A1 (de) Superlegierung auf nickelbasis, einkristalline schaufel und turbinenmotor
EP4359579A1 (de) Superlegierung auf nickelbasis, einkristalline schaufel und turbomaschine
EP3911774B1 (de) Nickelbasislegierung mit hoher mechanischer festigkeit bei hoher temperatur
FR3147571A1 (fr) Superalliage a base de nickel, aube monocristalline

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20240116

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20250212

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTC Intention to grant announced (deleted)
INTG Intention to grant announced

Effective date: 20250602

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

Ref country code: CH

Ref legal event code: F10

Free format text: ST27 STATUS EVENT CODE: U-0-0-F10-F00 (AS PROVIDED BY THE NATIONAL OFFICE)

Effective date: 20251008

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602022022693

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20251008

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1844836

Country of ref document: AT

Kind code of ref document: T

Effective date: 20251008

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20251008