EP3578676A1 - Austenitische legierung mit hohem aluminiumgehalt und assoziiertes designverfahren - Google Patents

Austenitische legierung mit hohem aluminiumgehalt und assoziiertes designverfahren Download PDF

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Publication number
EP3578676A1
EP3578676A1 EP19179103.7A EP19179103A EP3578676A1 EP 3578676 A1 EP3578676 A1 EP 3578676A1 EP 19179103 A EP19179103 A EP 19179103A EP 3578676 A1 EP3578676 A1 EP 3578676A1
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Prior art keywords
alloy
nickel
chromium
aluminum
niobium
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EP19179103.7A
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English (en)
French (fr)
Inventor
Mathieu COUVRAT
Antoine FACCO
Cristelle PAREIGE
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Centre National de la Recherche Scientifique CNRS
Institut National des Sciences Appliquees de Rouen
Universite de Rouen Normandie
Manoir Pitres SAS
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Centre National de la Recherche Scientifique CNRS
Institut National des Sciences Appliquees de Rouen
Universite de Rouen Normandie
Manoir Pitres SAS
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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
    • 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
    • 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
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/44—Ferrous alloys, e.g. steel alloys containing chromium with nickel with molybdenum or tungsten
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/48—Ferrous alloys, e.g. steel alloys containing chromium with nickel with niobium or tantalum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
    • C22C38/50—Ferrous alloys, e.g. steel alloys containing chromium with nickel with titanium or zirconium

Definitions

  • the present invention relates to the field of austenitic alloys requiring good mechanical and environmental resistance, at high temperatures, in particular for use in steam cracking furnaces in the petrochemical industry.
  • it relates to a high aluminum content austenitic alloy which exhibits excellent corrosion and creep resistance at temperatures above 900 ° C.
  • Austenitic alloys based on nickel, chromium and iron called “refractory” have been known for many years for their applications at very high temperatures (see in particular the document FR2333870 ).
  • refractory a metallic oxide layer on its surface
  • aluminum oxide layer Due to the formation of an aluminum oxide layer on its surface, the alloy then has excellent resistance to carburization and oxidation in an environment at very high temperatures.
  • an austenitic alloy having a high aluminum content to ensure high environmental resistance (corrosion by carburization, oxidation or nitriding) while guaranteeing a creep resistance at least as high as the alloys currently known. , containing little (typically less than 3%) or no aluminum.
  • the present invention proposes a solution for achieving the aforementioned objectives.
  • the invention relates to a high aluminum austenitic alloy which has excellent environmental and creep resistance at temperatures of 900 ° C or higher.
  • the invention also relates to a method for designing such an alloy.
  • the method comprises the choice of the respective weight percentages of aluminum x Al, nickel x Ni , chromium x Cr , titanium x Ti , carbon x C , niobium x Nb , tantalum x Ta , silicon x Si and manganese x Mn , so that the alloy has less than 1% by volume of a B2-NiAl intermetallic phase and less than 1% by volume of a chromium rich alpha prime phase, after the service temperature has been applied to him.
  • the invention relates to an austenitic alloy based on nickel, chromium and iron, with a high aluminum content, intended to be used at a service temperature Ts between 900 ° C. and 1200 ° C. Ts can typically be set to 1000 ° C.
  • austenitic alloy according to the invention could be used at operating temperatures below 900 ° C, but would not have, in these temperature ranges, significant advantage over a standard alloy containing little or no 'aluminum.
  • a minimum of 20% chromium is required to ensure good resistance to corrosion and to allow the formation of chromium carbides, which favorably impact the creep resistance of the alloy.
  • the maximum mass percentage of chromium is constrained to 32% in particular to limit the integration of alphagene element tending to destabilize the austenitic structure of the alloy.
  • the type of primary carbides (M 7 C 3 or M 23 C 6 ), predominant after solidification of the alloy, varies depending on the chromium content, as illustrated in FIG. figure 4 . It is observed that the molar fraction of the primary carbides M 7 C 3 passes through an optimum for a chromium content between 23% and 28%, then decreases, whereas the molar fraction of the primary carbides M 23 C 6 increases significantly beyond a chromium content of the order of 30%.
  • the weight percentage of chromium is thus kept below 30%, or even less than 28%, so as to guarantee a majority fraction of M 7 C 3 primary carbides after solidification of the alloy, which make it possible to obtain a thin and homogeneous dispersion of M 23 C 6 secondary carbides (from the transformation of primary carbides M 7 C 3 during high temperature cycles).
  • Such a dispersion of secondary precipitates M 23 C 6 (thinner and uniformly distributed than the primary carbides M 23 C 6 ) provides improved creep properties to the alloy.
  • the minimum mass percentage of nickel is defined at 30% so as to maintain a refractory alloy of austenitic structure, the alloy containing at least 20% of chromium as well as other alphagenic elements tending to destabilize the austenitic structure in favor of a ferritic structure.
  • the amount of nickel is limited to 60%, or even 55% for economic reasons, nickel being a strong contributor of costs.
  • the range of nickel content can be defined for a purpose just necessary, to prevent the formation of harmful phases at the service temperature Ts while maintaining controlled costs, as will be described later.
  • the mass percentage of carbon is defined at a minimum of 0.4% to allow formation in the alloy of a large volume fraction of carbides, said carbides reinforcing the creep resistance of the alloy.
  • the maximum percentage is set at 0.7% in order to maintain sufficient ductility in the use of the material, carbide reinforcement also having a reduced ductility effect.
  • Titanium has a strong impact on the formation of finer and uniformly distributed carbides in the alloy: it is particularly effective at low levels, called micro additions. It is included in the alloy in a mass percentage ranging from 0.05% to 0.3%.
  • Niobium and / or tantalum are added to the alloy. These two compounds also contribute to the formation of carbides.
  • the sum of the mass percentages of niobium and tantalum is greater than 0.6% and less than or equal to 2%.
  • Aluminum is present in the alloy at a high content, between 3.5% and 6%. Such a content allows the formation of a continuous aluminum oxide layer on the surface of the alloy in a wide range of oxygen partial pressure (ranging from less than 5 particles per million to high partial pressures such as under air), and a wide temperature range (intermediate temperatures around 800 ° C to temperatures above 1200 ° C). The surface layer of aluminum oxide then forms a very resistant and effective barrier to corrosion (oxidation, carburization, nitriding) of the alloy, at high temperatures, typically 900 ° C. and above.
  • the weight percentage of aluminum is greater than or equal to 3.8% or even 4%.
  • a high aluminum content ensures the formation of an aluminum oxide layer over a wider range of environmental conditions. It also allows access to a larger "reservoir” of aluminum and thus to preserve the properties of the alloy over longer durations, in very severe environments where the aluminum oxide layers are consumed.
  • an element composed of at least one rare earth (such as, for example, yttrium, cerium) and / or hafnium is beneficial to the growth and adhesion of the oxide layer. aluminum on the surface of the alloy.
  • the total amount of this element is set at a minimum of 0.002%. An amount greater than 0.1% does not bring any additional effect whereas it implies a strong impact on the cost; it can even be harmful to mechanical properties, including high mechanical resistance temperatures.
  • the total content of rare earth (s) and / or hafnium is limited to 0.05%, or even limited to 0.01%.
  • the alloy may optionally contain silicon, to promote flow during casting of the alloy and enhance its resistance to corrosion.
  • the amount of silicon is nevertheless limited to 0.5% to avoid negatively impacting the creep resistance of the alloy.
  • the alloy may also contain manganese, but in a mass percentage of less than 0.5% to avoid or limit the formation of spinel oxide of manganese and chromium which has a very fast formation kinetics but is less stable and protective than chromium oxide and even more so than aluminum oxide.
  • the alloy may optionally contain tungsten, which plays a minor role in improving the mechanical properties at high temperatures, by processing the tungsten enriched chromium carbides and by solid solution hardening. This element is limited to 2% because too much tungsten in the chromium carbides will make them lose their stability and their role of hardening at high temperatures.
  • the alloy comprises iron, in a percentage complementing the composition of the alloy, so that the sum of the mass percentages of the compounds reaches 100%.
  • the alloy may also comprise low levels of other conventional elements of steels found in particular in the raw materials or in the manufacturing steps. At low levels, these elements have little impact or special need. We thus find at levels less than 0.5% of elements such as molybdenum or copper.
  • the alloy can possibly be polluted by trace impurities of the order of the particle per million, to the hundreds of particles per million, such as phosphorus, sulfur, lead, tin, etc. .
  • the operating temperature is the temperature at which the alloy is intended to be subjected during its use: for example, for an alloy forming a steam cracking furnace tube, the operating temperature may be between 950 ° C and 1150 ° C.
  • B2 according to the notation Strukturbericht qualifies a phase comprising two types of atoms (here, Ni and Al) in equal proportion and whose crystallographic structure is "Interpenetrated primitive cubic", that is to say that each of the two types of atoms forms a simple centered cubic network, with one atom of one type in the center of each cube of the other type.
  • the B2-NiAl phase is not necessarily stoichiometric, the Al sites may possibly be replaced by Cr or Fe atoms.
  • the Applicant has been able to determine that, in a high aluminum austenitic alloy, the creep resistance, at the service temperature Ts, decreases with the increase of the volume fraction of the B2-NiAl phase in the alloy. brought to said temperature. It is the same with the increase of the volume fraction of alpha prime phases.
  • a characteristic of the austenitic alloy according to the invention is that it has less than 1% by volume of a B2-NiAl intermetallic phase and less than 1% by volume of a phase rich in chrome alpha prime, after the service temperature Ts has been applied to it for a few hours, typically for more than 10 hours.
  • the alloy according to the invention has less than 0.5% by volume of each of the B2-NiAl and alpha prime phases, or even less than 0.2% by volume.
  • Mass percentages in the alloy of aluminum x Al, nickel x Ni , chromium x Cr , titanium x Ti , carbon x C , niobium x Nb , tantalum x Ta and (when present) silicon x Si and manganese x Mn are linked to T max B 2 - NiAl and T max ⁇ ' , the maximum temperatures of the stability domain respectively of the B2-NiAl intermetallic phase and of the alpha prime phase, in the alloy. Said maximum temperatures of the stability range can be seen as the limiting temperatures below which there is formation in the alloy of the phases B2-NiAl and alpha prime over a temperature range corresponding to the stability range of each phase.
  • the compounds Al, Cr, Si, Mn, Ti, Nb and Ta tend to increase the maximum temperatures T max B 2 - NiAl and T max ⁇ ' from the stability domain of the B2-NiAl and alpha prime phases (in other words, they tend to widen their field of existence towards high temperatures); the compounds Ni and C tend to decrease the maximum temperatures T max B 2 - NiAl and T max ⁇ ' the stability domain of the B2-NiAl and alpha prime phases.
  • the service temperature Ts must be greater than the maximum temperatures T max B 2 - NiAl and T max ⁇ ' stability domains of the B2-NiAl phase and the alpha prime phase, so that the alloy, subjected to Ts during its use, exhibits no or very few intermetallic phase precipitates B2-NiAl and / or alpha premium, which may reduce its resistance to creep.
  • the weight percentages of aluminum x Al, nickel x Ni , chromium x Cr , titanium x Ti , carbon x C , niobium x Nb , tantalum x Ta and when they are present, silicon x Si and manganese x Mn thus respect one and the other of the two following relations R3, R4: - 28 , 3 x al 2 + 455 , 4 x al - 0 , 32 x Or 2 + 15 , 3 x Or - 0 , 22 x Cr 2 + 20 , 7 x Cr + 121 x Yes + 27 x mn + 16 x Ti + 12 x Nb + 16 x Your - 45 x C - 866 ⁇ ts 1 , 8 x al 2 + 38 , 3 x al + 0 , 42 x Or 2 - 51.2 x Or + 27.8 x Cr + 34 x Yes + 8 x mn + 89
  • the alloys forming the tubes can be subjected to temperatures ranging from 950 ° C to 1150 ° C.
  • a service temperature Ts of 1000 ° C may for example be taken into account in the above relationships to cover a large part of industrial cases.
  • X is a minimum value for the alloy to have very little or no B2-NiAl phases and alpha prime at the service temperature Ts.
  • An upper bound is defined at X plus 10 points (X + 10), to leave an industrial latitude over the control of the composition. More nickel does not bring additional benefits and unnecessarily increases the costs of the alloy. Alternatively, the upper bound could be set to X + 8 or even X + 6.
  • the invention also relates to a method for designing an austenitic alloy with a high aluminum content and having excellent resistance to both corrosion and creep at a service temperature greater than or equal to 900 ° C.
  • the design process includes the choice of the respective weight percentages of aluminum x Al, nickel x Ni , chromium x Cr , titanium x Ti , carbon x C , niobium x Nb , tantalum x Ta , and they are present, silicon x Si , manganese x Mn and tungsten x W so that the alloy has less than 1%, even less than 0.5%, or even less than 0.2% by volume of a B2-NiAl intermetallic phase and / or an alpha prime phase, after the service temperature Ts has been applied to it for a few hours.
  • the respective weight percentages of aluminum x Al, nickel x Ni , chromium x Cr , titanium x Ti , carbon x C , niobium x Nb , tantalum x Ta , and if they are present, silicon x Si and manganese x Mn are chosen so as to respect one of the two following relations R3, R4: - 28 , 3 x al 2 + 455 , 4 x al - 0 , 32 x Or 2 + 15 , 3 x Or - 0 , 22 x Cr 2 + 20 , 7 x Cr + 121 x Yes + 27 x mn + 16 x Ti + 12 x Nb + 16 x Your - 45 x C - 866 ⁇ ts 1 , 8 x al 2 + 38 , 3 x al + 0 , 42 x Or 2 - 51.2 x Or + 27.8 x Cr + 34 x Yes + 8 x
  • X is a minimum value for the alloy to have very little or no B2-NiAl phases and alpha prime at the service temperature Ts.
  • An upper bound is defined at X + 10 because more nickel does not bring additional benefits and unnecessarily increases the costs of the alloy; the upper limit could possibly be set to X + 8 or even X + 6.
  • the alloys forming the tubes are usually subjected to temperatures ranging from 950 ° C to 1150 ° C.
  • Service temperatures Ts of 950 ° C, 1000 ° C or 1050 ° C may be the most commonly considered.
  • the invention also relates to a method for validating the compatibility of a high aluminum austenitic alloy with a service temperature Ts defined between 900 ° C and 1200 ° C.
  • Compatible alloy means an alloy having excellent resistance to corrosion or creep, said service temperature Ts or above.
  • the validation process includes verifying that the alloy is free or less than 1%, or even less than 0.5%, or even less than 0.2% by volume B2-NiAl intermetallic phase and alpha prime after the temperature service Ts was applied to him for a few hours (typically 10 hours).
  • the respective weight percentages of aluminum x Al, nickel x Ni , chromium x Cr , titanium x Ti , carbon x C , niobium x Nb , tantalum x Ta and if present, silicon x Si and manganese x Mn , in the alloy are measured (for example by spark spectrometry); the following relations are then applied so as to check the compatibility of the alloy with a determined service temperature Ts: - 28 , 3 x al 2 + 455 , 4 x al - 0 , 32 x Or 2 + 15 , 3 x Or - 0 , 22 x Cr 2 + 20 , 7 x Cr + 121 x Yes + 27 x mn + 16 x Ti + 12 x Nb + 16 x Your - 45 x C - 866 ⁇ ts 1 , 8 x al 2 + 38 , 3 x al + 0 , 42 x Or 2 - 51.2
  • the alloy is compatible with the determined service temperature Ts. If at least one inequality is not respected, the alloy is identified as not compatible with the determined service temperature Ts; said alloy may potentially be identified compatible with a higher service temperature Ts.
  • alloys described below have a high aluminum content (greater than 3.5%), their high environmental resistance has been verified and is considered assured.
  • the creep resistance of the alloys presented as examples (Table 1) was evaluated using creep tests at 1050 ° C. under a constant stress of 17 MPa, the tests being carried out on samples taken from parts made in the various alloys. . From these tests, a deformation curve (percentage of deformation of the sample) as a function of time is extracted, and a time at break t R , to arrive at the rupture of the sample.
  • the time at break t R of the different samples is compared with the time at break t Rref of an alloy based on nickel, chromium and iron known and used for applications petrochemical steam crackers, whose trade name is Manaurite® XTM.
  • the composition of the alloys numbered from 1 to 8 is detailed in Table 1.
  • the composition of the reference alloy Manaurite XTM, denoted "Ref”, is also described in Table 1.
  • the time at break t Rref of the Reference alloy under the creep test conditions considered is 1095 hours.
  • the resistance of an alloy in the context of the present examples is therefore considered very good if the time at break t R is in the same range of values, greater than or equal to 1000h.
  • the alloys referenced 1 to 8 of Table 1 comprise mass percentages of aluminum ranging from 3.5% to 5.6%.
  • the other compounds of each alloy 1 to 8 have mass percentages included in the foregoing ranges for an alloy according to the invention, as can be seen in Table 1.
  • T max B 2 - NiAl and T max ⁇ ' B2-NiAl and alpha prime intermetallic phase stability domain can be calculated from the mass percentages of the compounds aluminum, nickel, chromium, titanium, carbon , niobium, tantalum and when present, silicon and manganese, according to the relations R1, R2 established by the plaintiff:
  • T max B 2 - NiAl ° C - 28 , 3 x al 2 + 455 , 4 x al - 0 , 32 x Or 2 + 15 , 3 x Or - 0 , 22 x Cr 2 + 20 , 7 x Cr + 121 x Yes + 27 x mn + 16 x Ti + 12 x Nb + 16 x Your - 45 x C - 866
  • T max ⁇ ' ° C 1 , 8 x al 2 + 38 , 3 x al + 0 , 42 x Or 2 - 51.2 x Or
  • T max B 2 - NiAl and T max ⁇ ' also appear on the phase diagrams resulting from CALPHAD simulations presented in FIGS. 1a to 1d: the stability domain of the B2-NiAl phase is represented by the recessed round symbol curve, the stability domain of the alpha-prime phase is represented by the black cross-symbols curve.
  • the alloys 1 to 8 respectively have a maximum temperature T max B 2 - NiAl of 822.1 ° C, 906 ° C, 1079.6 ° C, 961.9 ° C, 1127.8 ° C, 1175.2 ° C, 988.2 ° C, 1255.2 ° C and respectively a maximum temperature T max ⁇ ' 878.6 ° C, 895 ° C, 1158.3 ° C, 907.1 ° C, 1098.4 ° C, 1120.1 ° C, 858.7 ° C, 961.2 ° C.
  • alloys 1 and 2 For a service temperature of 950 ° C, alloys 1 and 2 respect both relationships T max B 2 - NiAl ⁇ ts and T max ⁇ ' ⁇ ts , they therefore do not have phases B2-NiAl and alpha prime at the service temperature Ts and are in accordance with the invention.
  • the alloys 3, 4, 5, 6, 7 and 8 do not respect the two relations mentioned above, and therefore do not comply with the invention, for an operating temperature of 950 ° C.
  • alloys 1, 2, 4 and 7 respect both relationships T max B 2 - NiAl ⁇ ts and T max ⁇ ' ⁇ ts , and are in accordance with the invention.
  • the figure 2a shows that the alloy 4 (sample from the creep test at 1050 ° C, characterized physically post mortem, for example), has no B2-NiAl intermetallic phase, or alpha prime phase, after the temperature 1050 ° C has been applied to it. Only the classical phases are observed: carbides M 23 C 6 in an austenitic matrix. The initial M 7 C 3 primary interdendritic carbides were converted into M 23 C 6 secondary carbides, accompanied by a fine precipitation of M 23 C 6 secondary carbides (black zones).
  • Alloys 1, 2, 4 and 7 have break times t R between 1000h and 1351h (Table 1), which corresponds to excellent creep resistance.
  • Table 1 The figure 3 presents the deformation of a sample of the alloy 4 during the creep test, as a function of time.
  • the alloy 4 according to the invention for a service temperature Ts of 1050 ° C. undergoes only a very small deformation at 1050 ° C. under stress for at least the first 1000 hours.
  • Alloys 3, 5, 6 and 8 do not respect one or both of the two relationships T max B 2 - NiAl ⁇ ts and T max ⁇ ' ⁇ ts , and are not in accordance with the invention for a service temperature of 1000 ° C or 1050 ° C.
  • the Figures 2b, 2c and 2d show respectively that the alloys 5, 6 and 8 (samples from the creep test at 1050 ° C, characterized physically post mortem, by way of example) comprise B2-NiAl precipitates after the temperature of 1050 ° C was applied.
  • This B2-NiAl intermetallic phase could be identified as such thanks to fine characterizations carried out by transmission electron microscopy (TEM).
  • TEM transmission electron microscopy
  • the B2-NiAl phase appeared under two different types in alloys 6 ( Figure 2c ) and 8 ( figure 2d ): a type I having a flat shape in the austenitic matrix, formed by homogeneous germination; and a type II present between the carbide precipitates and the austenitic matrix, formed by heterogeneous germination.
  • the alpha prime phase rich in chromium has also been identified by TEM, essentially precipitating at the B2-NiAl / matrix interfaces and in the form of nano-precipitates
  • the alloys 3, 5, 6 and 8 have break times t R between 47h and 500h, which corresponds to a mechanical resistance well below the reference referred to.
  • the figure 3 presents the deformation of a sample of each of the alloys 5, 6 and 8 during the creep test as a function of time. They undergo significant deformation at 1050 ° C under stress during the first 250 hours.
  • the austenitic alloy with a high aluminum content according to the invention must comprise the compounds stated, in percentages by weight included in the stated ranges, and contain only one low volume fraction (less than or equal to 1%) or not at all of the B2-NiAl and alpha prime intermetallic phases, after the determined service temperature Ts has been applied thereto.
  • the relationships established by the applicant also advantageously make it possible to choose the mass percentage of nickel as a function of the other alloy compounds and the service temperature Ts, in a range ensuring the high resistance to creep of the alloy while limiting unnecessary costs of too much of this compound.
  • the austenitic alloys according to the invention can find applications in the field of petrochemicals (steam-cracking furnaces), in any other high-temperature application, typically greater than or equal to 900 ° C. combining problems of resistance to the environment and the environment. creep.

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EP19179103.7A 2018-06-07 2019-06-07 Austenitische legierung mit hohem aluminiumgehalt und assoziiertes designverfahren Pending EP3578676A1 (de)

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CN112011713B (zh) * 2020-08-30 2021-11-23 中南大学 一种消除3d打印镍基高温合金裂纹的方法
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