WO2019097163A1 - Superalliage a base de nickel, aube monocristalline et turbomachine - Google Patents
Superalliage a base de nickel, aube monocristalline et turbomachine Download PDFInfo
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- WO2019097163A1 WO2019097163A1 PCT/FR2018/052840 FR2018052840W WO2019097163A1 WO 2019097163 A1 WO2019097163 A1 WO 2019097163A1 FR 2018052840 W FR2018052840 W FR 2018052840W WO 2019097163 A1 WO2019097163 A1 WO 2019097163A1
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- nickel
- superalloy
- hafnium
- rhenium
- chromium
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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%
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- 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
Definitions
- the present disclosure relates to nickel-based superalloys for gas turbines, especially for stationary blades, also called distributors or rectifiers, or mobile gas turbine, for example in the field of aeronautics.
- nickel-based superalloys for monocrystalline blades have undergone significant changes in chemical composition, in particular to improve their creep properties at high temperature while maintaining environmental resistance. very aggressive in which these superalloys are used.
- metal coatings adapted to these alloys have been developed to increase their resistance to the aggressive environment in which these alloys are used, including the oxidation resistance and corrosion resistance.
- a ceramic coating of low thermal conductivity, fulfilling a thermal barrier function may be added to reduce the temperature at the surface of the metal.
- a complete protection system comprises at least two layers.
- the first layer also called underlayer or bonding layer
- the first layer is directly deposited on the nickel alloy superalloy to protect part, also called substrate, for example a blade.
- the deposition step is followed by a diffusion step of the underlayer in the superalloy.
- Depositing and broadcasting can also be done in a single step.
- the second layer generally called thermal barrier or "TBC” according to the acronym for "Thermal Barrier Coating” is a ceramic coating comprising for example yttria zirconia, also called “YSZ” according to the acronym English for “Yttria Stabilized Zirconia” or “YPSZ” according to the acronym for "Yttria Partially Stabilized Zirconia” and having a porous structure.
- TBC thermal barrier
- This layer can be deposited by various processes, such as electron beam evaporation (“EB-PVD” according to the acronym for “Electron Beam Physical Vapor Deposition”), the thermal projection (“APS”) according to the acronym for “Atmospheric Plasma Spraying” or “SPS” according to the acronym for “Suspension Plasma Spraying”), or any other method for obtaining a porous ceramic coating with low thermal conductivity.
- EB-PVD electron beam evaporation
- APS thermal projection
- SPS Stension Plasma Spraying
- foundry defects are likely to form in the parts, such as blades, during their manufacture by directed solidification. These defects are generally parasitic grains of the "Freckle" type, the presence of which can cause a premature rupture of the part in service. The presence of these defects, related to the chemical composition of the superalloy, generally leads to the rejection of the part, which leads to an increase in the cost of production.
- the present disclosure aims to provide nickel-based superalloy compositions for the manufacture of monocrystalline components, having improved performance in terms of service life and mechanical strength and to reduce the costs of production of the part (reduction of the scrap rate) compared to existing alloys.
- These superalloys have a higher high temperature creep resistance than existing alloys while showing good microstructural stability in the superalloy volume (low sensitivity to PTC formation), good microstructural stability under the coating undercoat.
- the thermal barrier low sensitivity to the formation of ZRS
- 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 comprising, in percentages by weight, 4.0 to 5.5% of rhenium, 3.5 to 12.5% cobalt, 0.30 to 1 , 50% molybdenum, 3.5 to 5.5% chromium, 3.5 to 5.5% tungsten, 4.5 to 6.0% aluminum, 0.35 to 1.50% titanium , 8.0 to 10.5% of tantalum, 0.15 to 0.30% of hafnium, preferably 0.16 to 0.30% of hafnium, preferably 0.17 to 0.30% of hafnium, preferably 0.18 to 0.30% hafnium, still more preferably 0.20 to 0.30% hafnium, 0.05 to 0.15% silicon, preferably 0.08 to 0.12% silicon , more preferably 0.10% of silicon, the balance consisting of nickel and unavoidable impurities.
- This superalloy is intended for the manufacture of monocrystalline gas turbine components, such as blades or mobile blades.
- Ni nickel-based superalloy
- This alloy therefore has an improved high temperature creep resistance. This alloy also has improved resistance to corrosion and oxidation.
- These superalloys have a density of less than or equal to 9.00 g / cm 3 (gram per cubic centimeter).
- a nickel-based superalloy monocrystalline part is obtained by a solidification process directed under a thermal gradient in a lost wax foundry.
- the nickel-based monocrystalline superalloy comprises an austenitic matrix of face centered cubic structure, nickel-based solid solution, called gamma phase ("y").
- This matrix contains gamma prime hardening phase precipitates ("G '") of ordered cubic structure Ll 2 of type N AI.
- the set (matrix and precipitates) is therefore described as a superalloy g / g '.
- this composition of the nickel-based superalloy allows the implementation of a heat treatment which restores the phase precipitates g 'and the eutectic phases g / g' which are formed during the solidification of the superalloy. It is thus possible to obtain a nickel-based monocrystalline superalloy containing controlled size precipitates, preferably of between 300 and 500 nanometers (nm), and containing a small proportion of eutectic phases g / g '.
- the heat treatment also makes it possible to control the volume fraction of the phase precipitates g 'present in the monocrystalline superalloy based on nickel.
- the volume percentage of the phase precipitates g ' 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), titanium ( Ti) and tantalum (Ta).
- the minor addition elements are hafnium (Hf) and silicon (Si), for which the maximum mass content is less than 1% by weight.
- unavoidable impurities include sulfur (S), carbon (C), boron (B), yttrium (Y), lanthanum (La) and cerium (Ce).
- Unavoidable impurities are those elements that are not intentionally added to the composition and that are provided with other elements.
- tungsten, chromium, cobalt, rhenium or molybdenum mainly serves to reinforce the austenitic matrix Y of face-centered cubic crystal structure (cfc) by hardening in solid solution.
- Rhenium slows the diffusion of chemical species within the superalloy and limit the coalescence of phase precipitates g 'during service at high temperature, which causes a reduction in mechanical strength. Rhenium thus makes it possible to improve the creep resistance at high nickel-based superalloy temperature.
- an excessively high concentration of rhenium can precipitate PTC intermetallic phases, for example phase s, phase P or phase m, which have a negative effect on the mechanical properties of the superalloy. Too high a concentration of rhenium can also cause the formation of a secondary reaction zone in the superalloy under the underlayer, which has a negative effect on the mechanical properties of the superalloy.
- the simultaneous addition of silicon and hafnium makes it possible to improve the resistance to hot oxidation of nickel-based superalloys by increasing the adhesion of the layer of alumina (Al2O3) that forms on the surface. superalloy at high temperature.
- This alumina layer forms a surface passivation layer 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 without also adding silicon or conversely add silicon without also adding hafnium and still improve the resistance to hot oxidation of the superalloy.
- chromium or aluminum makes it possible to improve the resistance to oxidation and corrosion at high temperature of the superalloy.
- chromium is essential for increasing the hot corrosion resistance of nickel-based superalloys.
- an excessively high content of chromium tends to reduce the solvus temperature of the phase y 'of the nickel-based superalloy, that is to say the temperature above which the phase y' is totally dissolved in the matrix y, which is undesirable.
- the chromium concentration is between 3.5 and 5.5% by weight in order to maintain a high solvus temperature of the phase y 'of the nickel-based superalloy, for example greater than or equal to 1250 ° C., but also to avoid the formation of topologically compact phases in the highly saturated matrix y in alloying elements such as rhenium, molybdenum or tungsten.
- cobalt which is a nickel-like element and which partially replaces nickel, forms a solid solution with the nickel in the y-matrix. Cobalt strengthens matrix y, reduces sensitivity to PTC precipitation and ZRS formation in the superalloy under the protective coating. However, an excessively high cobalt content tends to reduce the solvation temperature of the y phase of the nickel-based superalloy, which is undesirable.
- refractory elements such as molybdenum, tungsten, rhenium or tantalum slows down the mechanisms controlling the creep of superalloys based on nickel and which depend on the diffusion of chemical elements in the superalloy. .
- a very low sulfur content in a nickel-based superalloy makes it possible to increase the resistance to oxidation and hot corrosion as well as the resistance to flaking of the thermal barrier.
- a low sulfur content less than 2 ppm by weight (parts per million by weight), or ideally less than 0.5 ppm by weight, makes it possible to optimize these properties.
- Such a mass content of sulfur can be obtained by developing a low-sulfur mother batch or by a desulfurization process carried out after the casting. In particular, it is possible to maintain a low sulfur content by adapting the process for producing the superalloy.
- the superalloy may comprise, in percentages by weight, 4.0 to 5.5% of rhenium, 3.5 to 8.5% of cobalt, 0.30 to 1.50% of molybdenum, 3.5 to 5% of , 5% chromium, 3.5 to 4.5% tungsten, 4.5 to 6.0% aluminum, 0.50 to 1.50% titanium, 8.0 to 10.5% tantalum ,
- hafnium 0.15 to 0.30% of hafnium, preferably 0.17 to 0.30% of hafnium, still more preferably 0.20 to 0.30% of hafnium, 0.05 to 0.15% of silicon, the remainder being nickel and inevitable impurities.
- the superalloy may comprise, in percentages by weight,
- rhenium 3.5 to 12.5% cobalt, 0.30 to 1.50% molybdenum, 3.5 to 5.5% chromium, 3.5 to 5, 5% tungsten, 5.0 to 6.0% aluminum, 0.35 to 1.50% titanium, 8.0 to 10.5% tantalum, 0.15 to 0.30% hafnium, preferably 0.17 to 0.30% hafnium, still more preferably 0.20 to 0.30% hafnium, 0.05 to 0.15% of silicon, the remainder being nickel and inevitable impurities.
- the superalloy may comprise, in percentages by weight,
- the superalloy may comprise, in percentages by weight,
- the superalloy may comprise, in percentages by weight,
- the superalloy may comprise, in percentages by weight,
- rhenium 6.0 to 8.0% cobalt, 0.30 to 1.00% molybdenum, 3.5 to 4.5% chromium, 4.5 to 5, 5% tungsten, 5.0 to 6.0% aluminum, 0.35 to 1.30% titanium, 8.0 to 9.0% tantalum, 0.15 to 0.30% hafnium, preferably 0.17 to 0.30% hafnium, more preferably 0.20 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and any impurities. .
- the superalloy may comprise, in percentages by weight, 4.0 to 5.0% of rhenium, 4.0 to 6.0% of cobalt, 0.30 to 1.00% of molybdenum, 4.5 to 5% by weight. , 5% chromium, 3.5 to 4.5% tungsten, 5.0 to 6.0% aluminum, 0.35 to 1.30% titanium, 8.0 to 10.5% tantalum ,
- hafnium 0.15 to 0.30% hafnium, preferably 0.17 to 0.30% hafnium, still more preferably 0.20 to 0.30% hafnium, 0.05 to 0.15% silicon, the remainder being nickel and unavoidable impurities.
- the superalloy may comprise, in percentages by weight, 5.2% of rhenium, 5.0% of cobalt, 0.50% of molybdenum, 4.0% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and inevitable impurities.
- the superalloy may comprise, in mass percentages, 5.2% of rhenium, 5.0% of cobalt, 0.50% of molybdenum, 4.0% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.17% hafnium, 0.10% silicon, the balance being nickel and unavoidable impurities.
- the superalloy may comprise, in mass percentages, 5.2% of rhenium, 5.0% of cobalt, 0.50% of molybdenum, 4.0% of chromium, 4.0% of tungsten, 5.1 % aluminum, 1.00% titanium, 10.0% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and unavoidable impurities.
- the superalloy may comprise, in mass percentages, 5.0% of rhenium, 12.0% of cobalt, 1.00% of molybdenum, 4.0% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and inevitable impurities.
- the superalloy may comprise, in mass percentages, 5.0% of rhenium, 4.0% of cobalt, 1.00% of molybdenum, 4.0% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and inevitable impurities.
- the superalloy may comprise, in percentages by weight, 4.9% of rhenium, 8.0% of cobalt, 1.00% of molybdenum, 4.2% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and inevitable impurities.
- the superalloy may comprise, in mass percentages, 4.9% of rhenium, 8.0% of cobalt, 1.00% of molybdenum, 4.2% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.17% hafnium, 0.10% silicon, the balance being nickel and unavoidable impurities.
- the superalloy may comprise, in percentages by weight, 4.9% of rhenium, 8.0% of cobalt, 1.00% of molybdenum, 4.2% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.16% hafnium, 0.10% silicon, the balance being nickel and unavoidable impurities.
- the superalloy may comprise, in mass percentages, 4.7% of rhenium, 7.0% of cobalt, 0.50% of molybdenum, 4.0% of chromium, 5.0% of tungsten, 5.4 % aluminum, 0.80% titanium, 8.5% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and unavoidable impurities.
- the superalloy may comprise, in mass percentages, 4.5% of rhenium, 5.0% of cobalt, 0.50% of molybdenum, 5.0% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and inevitable impurities.
- the superalloy may comprise, in percentages by weight, 4.5% of rhenium, 5.0% of cobalt, 0.50% of molybdenum, 5.0% of chromium, 4.0% of tungsten, 5.4 % aluminum, 0.55% titanium, 10.0% tantalum, 0.25% hafnium, 0.10% silicon, the balance being nickel and unavoidable impurities.
- the superalloy may comprise, in mass percentages, 4.3% of rhenium, 5.0% of cobalt, 0.50% of molybdenum, 4.0% of chromium, 4.0% of tungsten, 5.4 % aluminum, 1.00% titanium, 8.5%
- tantalum 0.25% hafnium, 0.10% silicon, the balance being nickel and unavoidable impurities.
- the present disclosure also relates to a monocrystalline blade for a turbomachine comprising a superalloy as defined above.
- This blade thus has an improved high temperature creep resistance.
- the blade may comprise a protective coating comprising a metal underlayer deposited on the superalloy and a ceramic thermal barrier deposited on the metal underlayer.
- the metal sub-layer 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 ceramic coating (based on zirconia) with a low thermal conductivity.
- the blade may have a structure oriented in a crystallographic direction ⁇ 001>.
- This orientation generally gives the optimum mechanical properties at dawn.
- the present disclosure also relates to a turbomachine comprising a blade as defined above.
- FIG. 1 is a schematic longitudinal sectional view of a turbomachine
- FIG. 2 is a graph representing the parameter NFP (FIG.
- FIG. 3 is a graph representing the volume fraction of phase y 'at different temperatures and for different superalloys.
- Nickel-based superalloys are intended for the manufacture of monocrystalline blades by a method of solidification directed in a thermal gradient.
- the use of a monocrystalline seed or a grain selector at the beginning of solidification makes it possible to obtain this monocrystalline structure.
- the structure is oriented for example in a ⁇ 001> crystallographic direction which is the orientation which generally gives the optimum mechanical properties to the superalloys.
- the solid nickel monocrystalline superalloys of solidification have a dendritic structure and consist of g 'Ni 3 precipitates (AI, Ti, Ta) dispersed in a matrix g of face-centered cubic structure, solid solution based on nickel. These phase precipitates g 'are heterogeneously distributed in the volume of the single crystal because of chemical segregations resulting from the solidification process. Furthermore, eutectic phases g / g 'are present in the inter-dendritic regions and constitute preferential sites for crack initiation. These eutectic phases g / g 'form at the end of solidification.
- the eutectic phases g / g ' are formed to the detriment of precipitated ends (size less than one micrometer) hardening phase g'.
- These g 'phase precipitates are the main source of hardening nickel-based superalloys.
- the presence of eutectic g / g 'residual phases does not optimize the hot creep resistance of the nickel-based superalloy.
- the solid nickel-based superalloys of solidification are therefore heat-treated to obtain the desired distribution of the different phases.
- the first heat treatment is a homogenization treatment of the microstructure which aims to dissolve the phase precipitates g 'and to eliminate the eutectic phases g / g' or to significantly reduce their volume fraction. This treatment is carried out at a temperature greater than the solvus temperature of the phase g 'and lower than the starting melting temperature of the superalloy (T so ndus) ⁇ A quenching is then performed at the end of this first heat treatment to obtain a fine and homogeneous dispersion of the precipitates g '. Thermal treatments of income are then carried out in two stages, at temperatures below solvate temperature of the phase g '. In a first step, to enlarge the precipitates g 'and obtain the desired size, then in a second step, to increase the volume fraction of this phase to about 70% at room temperature.
- FIG. 1 represents, in section along a vertical plane passing through its main axis A, a turbofan engine 10.
- the turbofan engine 10 comprises, from upstream to downstream according to the circulation of the air flow, a blower 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 blades 20A rotating with the rotor and 20B rectifiers (fixed vanes) mounted on the stator.
- the stator of the turbine 20 comprises a plurality of stator rings 24 arranged vis-à-vis the blades 20A of the turbine 20.
- a blade 20A or a rectifier 20B for a turbomachine comprising a superalloy as defined previously coated with a protective coating comprising a metallic undercoat
- a turbomachine may in particular be a turbojet such as a turbofan engine 10.
- the turbomachine may also be a single-jet turbojet, a turboprop or a turbine engine.
- Example 1 to Ex 10 Ten nickel-based monocrystalline superalloys of the present disclosure (Ex 1 to Ex 10) were studied and compared with four commercial monocrystalline superalloys CMSX-4 (Ex 11), CMSX-4PlusC (Ex 12), CMSX-10 ( Ex 13) and René N6 (Ex 14).
- the chemical composition of each of the monocrystalline superalloys is given in Table 1, the composition Ex 13 also comprising 0.10% by weight of niobium (Nb) and the composition Ex 14 further comprising 0.05% by weight of carbon (C) and 0.004% by weight of boron (B). All these superalloys are superalloys based on nickel, that is to say that the complement to 100% of the compositions presented consists of nickel and unavoidable impurities.
- the density at room temperature of each superalloy was estimated using a modified version of the Hull formula (F.C. Hull, Metal Progress, November 1969, ppl39-140).
- This empirical equation has been proposed by Hull.
- the empirical equation is based on the law of mixtures and includes corrective terms deduced from a linear regression analysis of experimental data (chemical compositions and measured densities) concerning 235 superalloys and stainless steels.
- This Hull formula has been modified to take into account elements such as rhenium and ruthenium.
- the modified Hull formula is:
- Dc, DM, ..., D x are the densities of the elements Cr, Ni, ..., X expressed in lb / in 3 (pounds per cubic inch) and D is the density of the superalloy expressed in g / cm 3 .
- % Cr,% Ni, ...% X are the contents, expressed in percentages by weight, of the elements of the superalloy Cr, Ni, ..., X.
- the densities calculated for the alloys of the invention and for the reference alloys are less than 9.00 g / cm 3 (see Table 2).
- Table 2 shows various parameters for superalloys Ex 1 to Ex 14.
- NFP [% Ta + 1.5% Hf + 0.5% Mo - 0.5%% Ti)] / [% W + 1.2% Re)]
- % Cr,% Ni, ...% X are the contents, expressed in percentages by weight, of the elements of the superalloy Cr, Ni, ..., X.
- the parameter NFP makes it possible to quantify the sensitivity to the formation of "Freckles" -specific grains during the directional solidification of the part (US Pat. No. 5,888,451). To avoid the formation of "Freckles" type defects, the NFP parameter must be greater than or equal to 0.7.
- the superalloys Ex 1 to Ex 10 all have an NFP parameter greater than or equal to 0.7 while the commercial superalloys Ex 11 to Ex 14 have a parameter NFP less than 0.7.
- phase compound y ' The intrinsic mechanical strength of the phase y 'increases with the content of elements that substitute for aluminum in the compound N13AI, such as titanium, tantalum and part of the tungsten.
- the RGP parameter makes it possible to estimate the level of hardening of the phase y ':
- Cn, C Ta , C w and C Ai are the respective atomic percentage concentrations of the elements Ti, Ta, W and Al in the superalloy.
- the parameter Md is defined as follows:
- Md ⁇ X i (Md) i
- Xi is the fraction of the element i in the superalloy expressed as an atomic percentage, (Md)
- Md is the value of the parameter Md for the element i.
- Table 3 shows the values of Md for the different elements of the superalloys.
- the sensitivity to the formation of PTC is determined by the Md parameter, according to the New PHACOMP method which was developed by Morinaga et al. (Morinaga et al., New PHACOMP and its application to alloy design, Superalloys 1984, edited by M Gell et al., The Metallurgical Society of AIME, Warrendale, PA, USA (1984) pp. 523-532). According to this model, the sensitivity of the superalloys to the formation of PTC increases with the value of the parameter Md.
- Ex 1 to Ex 14 have substantially equal values of the parameter Md. These superalloys thus have sensitivities similar to the formation of PTC, sensitivities that are relatively low.
- ZRS (%) is the linear percentage of ZRS in the superalloy under the coating and where the concentrations of the alloying elements are in atomic percentages.
- This equation (5) was obtained by multiple linear regression analysis from observations made after aging for 400 hours at 1093 ° C (centigrade) of samples of various alloys of compositions close to the composition Ex 12 under a NiPtAI coating.
- the values of the parameter [ZRS (%)] 1/2 are either negative or weakly positive, and these superalloys therefore have a low sensitivity to the formation of ZRS under a NitPtAI coating, as well as the commercial superalloy Ex 14 which is known for its low sensitivity to ZRS formation.
- the commercial superalloy EX 13 which is known to be very sensitive to the formation of ZRS under a NiPtAI coating, has a relatively high value of the [ZRS (%)] 1/2 parameter.
- ThermoCalc software (Ni25 database) based on the CALPHAD method was used to calculate the solvus temperature of the equilibrium phase y '.
- the superalloys Ex 1 to Ex 10 have a solvus temperature y 'greater than the solvus temperature y' Superalloys Ex 11, Ex 12 and Ex 14.
- ThermoCalc software (Ni25 database) based on the CALPHAD method was used to calculate the volume fraction (in percentage by volume) of phase y 'at equilibrium in the superalloys Ex 1 to Ex 14 at 950 ° C. , 1050 ° C and 1200 ° C.
- the superalloys Ex 1 to Ex 10 contain volume fractions of phase y 'which are greater than or comparable to the volume fractions of phase y' of commercial superalloys Ex 11 to Ex 14.
- the combination of a high solvus temperature y and high volume fractions of phase y 'for superalloys Ex 1 to Ex 10 is favorable to good resistance to creep at high temperature and very high temperature, for example. example at 1200 ° C. This resistance must be greater than the creep resistance of superalloys Ex 11 to Ex 14 and close to that of the Ex 13 superalloy commercial.
- ThermoCalc software (Ni25 database) based on the CALPHAD method was used to calculate the volume fraction (as a percentage by volume) of equilibrium phase s in the superalloys Ex 1 to Ex 14 at 950 ° C. and 1050 ° C (see Table 5).
- the chromium concentrations in the g phase are higher for the superalloys Ex 1 to Ex 10, compared to the chromium concentrations in the g phase for commercial superalloys Ex 12 to Ex 14, which is favorable to better resistance to corrosion and hot oxidation.
- the super alloys Ex 2, Ex 5, Ex 6 and Ex 10 have a better creep behavior than the Ex 11 and Ex 14 alloys.
- the Ex 13 superalloy also has good creep properties.
- the superalloys are subjected to one of the thermal cycles as described in INS-TTH-001 and INS-TTH-002: Oxidative Cycling Test Method (Mass Loss Test and Thermal Barrier).
- a specimen of the tested superalloy (peg having a diameter of 20 mm and a height of 1 mm) is subjected to thermal cycling, each cycle comprises a rise at 1150 ° C. in less than 15 minutes (minutes), a bearing at 1150 ° C for 60 min and a turbined cooling of the test piece for 15 min.
- the thermal cycle is repeated until observation of a loss of mass of the test piece equal to 20 mg / cm 2 (milligrams per square centimeter).
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Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
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RU2020119484A RU2780326C2 (ru) | 2017-11-14 | 2018-11-14 | Суперсплав на никелевой основе, монокристаллическая лопатка и турбомашина |
JP2020544982A JP7305662B2 (ja) | 2017-11-14 | 2018-11-14 | ニッケル基超合金、単結晶ブレード及びターボ機械 |
CA3081885A CA3081885A1 (fr) | 2017-11-14 | 2018-11-14 | Superalliage a base de nickel, aube monocristalline et turbomachine |
EP18821711.1A EP3710611B1 (fr) | 2017-11-14 | 2018-11-14 | Superalliage a base de nickel, aube monocristalline et turbomachine |
BR112020009492-7A BR112020009492B1 (pt) | 2017-11-14 | 2018-11-14 | Superliga à base de níquel, pá monocristalina, e, turbomáquina |
US16/763,713 US11268170B2 (en) | 2017-11-14 | 2018-11-14 | Nickel-based superalloy, single-crystal blade and turbomachine |
CN201880073598.3A CN111655881A (zh) | 2017-11-14 | 2018-11-14 | 镍基超级合金、单晶体叶片和涡轮机 |
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FR1760675A FR3073526B1 (fr) | 2017-11-14 | 2017-11-14 | Superalliage a base de nickel, aube monocristalline et turbomachine |
FR1760675 | 2017-11-14 |
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EP (1) | EP3710611B1 (fr) |
JP (1) | JP7305662B2 (fr) |
CN (1) | CN111655881A (fr) |
BR (1) | BR112020009492B1 (fr) |
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Publication number | Priority date | Publication date | Assignee | Title |
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US11873543B2 (en) | 2019-01-31 | 2024-01-16 | Safran | Nickel-based superalloy having high mechanical and environmental strength at high temperatures and low density |
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FR3108365B1 (fr) | 2020-03-18 | 2022-09-09 | Safran Helicopter Engines | Aube pour turbomachine comprenant un revetement anticorrosion, turbomachine comprenant l’aube et procede de depot du revetement sur l’aube |
FR3124195B1 (fr) * | 2021-06-22 | 2023-08-25 | Safran | Superalliage a base de nickel, aube monocristalline et turbomachine |
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JPH11310839A (ja) | 1998-04-28 | 1999-11-09 | Hitachi Ltd | 高強度Ni基超合金方向性凝固鋳物 |
WO2003080882A1 (fr) | 2002-03-27 | 2003-10-02 | National Institute For Materials Science | Superalliage a base de ni solidifie de maniere directionnelle et superalliage a cristal unique a base de ni |
RU2293782C1 (ru) | 2005-08-15 | 2007-02-20 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Никелевый жаропрочный сплав для монокристаллического литья и изделие, выполненное из него |
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- 2018-11-14 CA CA3081885A patent/CA3081885A1/fr active Pending
- 2018-11-14 BR BR112020009492-7A patent/BR112020009492B1/pt active IP Right Grant
- 2018-11-14 EP EP18821711.1A patent/EP3710611B1/fr active Active
- 2018-11-14 WO PCT/FR2018/052840 patent/WO2019097163A1/fr unknown
- 2018-11-14 JP JP2020544982A patent/JP7305662B2/ja active Active
- 2018-11-14 US US16/763,713 patent/US11268170B2/en active Active
- 2018-11-14 CN CN201880073598.3A patent/CN111655881A/zh active Pending
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---|---|---|---|---|
US11873543B2 (en) | 2019-01-31 | 2024-01-16 | Safran | Nickel-based superalloy having high mechanical and environmental strength at high temperatures and low density |
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JP7305662B2 (ja) | 2023-07-10 |
FR3073526B1 (fr) | 2022-04-29 |
BR112020009492A2 (pt) | 2020-10-13 |
EP3710611A1 (fr) | 2020-09-23 |
JP2021503045A (ja) | 2021-02-04 |
EP3710611B1 (fr) | 2024-01-10 |
FR3073526A1 (fr) | 2019-05-17 |
CA3081885A1 (fr) | 2019-05-23 |
RU2020119484A (ru) | 2021-12-15 |
US11268170B2 (en) | 2022-03-08 |
US20200299808A1 (en) | 2020-09-24 |
BR112020009492B1 (pt) | 2023-04-11 |
CN111655881A (zh) | 2020-09-11 |
RU2020119484A3 (fr) | 2021-12-15 |
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