EP3061841A1 - Lochkorrosionsbeständiger martensitischer rostfreier stahl - Google Patents

Lochkorrosionsbeständiger martensitischer rostfreier stahl Download PDF

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EP3061841A1
EP3061841A1 EP16156815.9A EP16156815A EP3061841A1 EP 3061841 A1 EP3061841 A1 EP 3061841A1 EP 16156815 A EP16156815 A EP 16156815A EP 3061841 A1 EP3061841 A1 EP 3061841A1
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Prior art keywords
alloy
percent
microstructure
martensitic
stainless steel
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EP16156815.9A
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French (fr)
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EP3061841B1 (de
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Theodore Francis MAJKA
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General Electric Co
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General Electric Co
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    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/005—Modifying the physical properties by deformation combined with, or followed by, heat treatment of ferrous alloys
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D6/00—Heat treatment of ferrous alloys
    • C21D6/004—Heat treatment of ferrous alloys containing Cr and Ni
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D6/00—Heat treatment of ferrous alloys
    • C21D6/007—Heat treatment of ferrous alloys containing Co
    • 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
    • C22C38/52—Ferrous alloys, e.g. steel alloys containing chromium with nickel with cobalt
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/001—Austenite
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/004—Dispersions; Precipitations
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/008—Martensite

Definitions

  • the subject matter disclosed herein generally relates to corrosion resistant stainless steels. More particularly, it relates to corrosion pitting resistant, martensitic, stainless steels, including those suitable for turbine rotating components.
  • the metal alloys used for rotating components of a gas turbine must have a combination of high strength, toughness, fatigue resistance and other physical and mechanical properties in order to provide the required operational properties of these machines.
  • the alloys used must also have sufficient resistance to various forms of corrosion and corrosion mechanisms, particularly pitting corrosion, due to the extreme environments in which turbines are operated, including exposure to various ionic reactant species, such as various species that include chlorides, sulfates, nitrides and other corrosive species. Corrosion can also diminish the other necessary physical and mechanical properties, such as the high cycle fatigue strength, by initiation of surface cracks that propagate under the cyclic thermal and stresses associated with operation of the turbine.
  • corrosion pitting is believed to be associated with various electrochemical reaction processes enabled by airborne deposits, especially corrosive species present in the deposits, and moisture from intake air on the airfoil surfaces. Electrochemically-induced corrosion pitting phenomena occurring at the airfoil surfaces can in turn result in cracking of the airfoils due to the cyclic thermal and operating stresses experienced by these components. High levels of moisture can result from various sources, including use in high moisture environments, such as facilities located near oceans or other bodies of water, as well as on-line water washing, fogging, evaporative cooling, or various combinations thereof, to enhance compressor efficiency.
  • Corrosive contaminants usually result from the environments in which the turbines are operating because they are frequently placed in highly corrosive environments, such as those near chemical or petrochemical plants, where various chemical species may be found in the intake air, or those at or near ocean coastlines or other saltwater environments where various sea salts may be present in the intake air, or combinations of the above, or in other applications where the inlet air contains corrosive chemical species.
  • stainless steel alloys suitable for use as turbine airfoils, particularly industrial gas turbine airfoils, in the operating environments described and having improved resistance to corrosion pitting are very desirable.
  • a forged, corrosion pitting resistant, martensitic, stainless steel alloy comprises, by weight: about 12.0 to about 16.0 percent chromium; greater than 16.0 to about 20.0 percent cobalt, about 6.0 to about 8.0 percent molybdenum, about 1.0 to about 3.0 percent nickel, about 0.020 to about 0.040 percent carbon; and the balance iron and incidental impurities.
  • a method of making a forged, martensitic, pitting corrosion resistant, stainless steel alloy includes providing a forged preform of martensitic, pitting corrosion resistant stainless steel alloy comprising, by weight: about 12.0 to about 16.0 percent chromium; greater than 16.0 to about 20.0 percent cobalt, about 6.0 to about 8.0 percent molybdenum, about 1.0 to about 3.0 percent nickel, about 0.020 to about 0.040 percent carbon; and the balance iron and incidental impurities.
  • the method also includes heating the forged preform to a solutionizing temperature for a time sufficient to form a solutionized microstructure.
  • the method further includes cooling the forged preform and solutionized microstructure to room temperature to form a martensitic microstructure. Yet further, the method includes heating the forged preform to a tempering temperature of about 600°F for a tempering time sufficient to form a tempered forged preform comprising a tempered martensitic microstructure. Still further, the method includes cooling the tempered forged preform to room temperature.
  • Corrosion pitting as described above is presently observed in service on front stage compressor airfoils.
  • the corrosion pitting resistant, martensitic, stainless steel alloys described herein provide an iron-based, pitting corrosion resistant material that is a significant enhancement for many heavy marine and industrial applications that are susceptible to corrosion pitting phenomena as described above, including front stage turbine compressor airfoils, in regards to service reliability, reduction of maintenance concerns and costs, and avoidance of unplanned downtime due to airfoil failures.
  • the stainless steel alloys described herein specifically have greater resistance to corrosion pitting than GTD-450 and GTD-450+ stainless steels.
  • the enhancements in pitting corrosion resistance of the alloys and methods of making them have significant commercial value.
  • An additional benefit of the corrosion pitting resistant iron-base alloys and methods of making them is that they do not require the addition of separate coatings for pitting corrosion protection.
  • the stainless steel alloys described herein are particularly configured and well suited for forging, particularly the forging of turbine airfoil articles
  • a forged, martensitic, stainless steel alloy includes, by weight: about 12.0 to about 16.0 percent chromium; greater than 16.0 to about 20.0 percent cobalt, about 6.0 to about 8.0 percent molybdenum, about 1.0 to about 3.0 percent nickel, about 0.020 to about 0.040 percent carbon; and the balance iron and incidental impurities. More particularly, the forged, martensitic, stainless steel alloy includes, by weight: about 13.5 to about 14.5 percent chromium; greater than 16.0 to about 20.0 percent cobalt, about 6.0 to about 6.5 percent molybdenum, about 1.0 to about 3.0 percent nickel, about 0.020 to about 0.30 percent carbon; and the balance iron and incidental impurities.
  • the forged, martensitic, stainless steel alloy includes, by weight: about 14 percent chromium; greater than 16.0 to about 20.0 percent cobalt, about 6.0 molybdenum, about 1.0 to about 3.0 percent nickel, about 0.025 carbon; and the balance iron and incidental impurities.
  • the stainless steel alloy composition is selected and configured to provide a martensitic microstructure by heat treatment as described herein.
  • the stainless steel alloy composition is selected and configured to provide a martensitic stainless steel alloy with a minimum tensile strength of about 150 ksi, a molybdenum content of greater than 6%, and a pitting resistance equivalent number, or PREN, of greater than about 31.8.
  • the stainless steel alloys disclosed herein achieve these corrosion and strength properties by a combination of compositional chemistry and heat treatment.
  • the stainless steel alloys disclosed herein exhibit exceptional resistance to corrosion pitting and may be heat treated to provide high strength and fracture toughness suitable for application as early stage turbine compressor airfoils (e.g. stages 1 through stage 5), including both blades and vanes, for industrial gas turbines.
  • the stainless steel alloys described herein obtain strength primarily from the development of a martensitic microstructure and solid solution strengthening in conjunction with the martensitic reaction, while also developing a predetermined amount of retained austenite and substantially no delta ferrite, which in an embodiment also includes no delta ferrite.
  • the pitting resistance equivalent number provides a guideline for comparing the pitting corrosion resistance of stainless steel alloys based on alloy chemistry.
  • the martensitic stainless steel alloys described herein have a PREN greater than about 31.8, and more particularly greater than about 33.3. In one embodiment, the PREN ranged from greater than about 31.8 to about 42.4, and more particularly about 33.3 to about 36.0.
  • the stainless steel alloys disclosed herein may be described as iron-based alloys comprising five alloy constituents, including Cr, Mo, Co, Ni, and C. All other elements are impurities incidental to the manufacture of stainless steel, and may include, in weight percent, Mn (0.25 max.), Al (0.03 max.), V (0.10 max.), Si (0.25 max.), S (0.005 max.), or P (0.02 max.), for example, and are kept below the maximum prescribed levels described herein to ensure the consistency of properties and microstructure from lot to lot. When balanced within the stated ranges the disclosed stainless steel alloys provide a martensitic microstructure with the desired strength and fracture toughness levels along with corrosion pitting resistance.
  • Cr is a required constituent and will be present in an amount sufficient to form a passive film of chromium oxide on the alloy surface.
  • Cr is present in an amount of at least about 11.5 weight percent.
  • Cr is present in an amount of about 12 to about 16 weight percent, and more particularly about 13.5 to about 14.5 weight percent, and even more particularly about 14 weight percent.
  • Mo has a larger effect than Cr on the corrosion pitting resistance of stainless steel.
  • Mo is present in an amount of about 6.0 to about 8.0 weight percent, and more particularly about 6.0 to about 6.5 weight percent, and even more particularly about 6 weight percent. At least about 6 weight percent is required to ensure sufficient resistance to pitting in marine, chloride environments. Studies have shown that Mo enhances the repassivation capability of stainless steel. Conventional high Mo content stainless steels are typically either ferritic grades or austenitic grades with high Ni levels.
  • Martensitic high Mo content stainless steels grades that have been investigated have generally focused on exploiting the ultra-high strength capabilities present in high-temperature tempered materials and have been designed and heat treated at high tempering temperatures, such as 1,100°F, for use at elevated operating temperatures.
  • high tempering temperatures such as 1,100°F
  • corrosion resistance and toughness is sacrificed at the high tempering temperatures due to the precipitation and formation of Mo-rich and Cr-rich intermetallic phases, which deplete the matrix of the corrosion resisting elements Mo and Cr.
  • a secondary hardening effect also occurs due to formation of these intermetallic compounds.
  • the intermetallic phases include the laves phase (Fe 2 Mo), Fe 7 Mo 6 , FeMo, the sigma phase (Fe-Cr-Mo), and a complex BCC chi phase (Fe-Cr-Mo). Cobalt does not participate in the phases associated with these precipitation reactions. These intermetallic phases also drastically decrease the toughness of the alloy. Thus, martensitic stainless alloys of this invention are tempered at low tempering temperatures as described herein to avoid the precipitation of these intermetallic phases. The tempered alloys are suitable for use in relatively lower temperature applications where corrosion resistance with moderate strength and good toughness are important.
  • the martensitic stainless alloys of this invention balance high Mo additions with the low-tempering temperature region of the hardness vs tempering temperature curve to avoid the formation of intermetallic phases and keep Mo and Cr in solution to maintain a high level as toughness.
  • the microstructure of the martensitic stainless steel alloys of this invention contains substantially no laves phase, which in an embodiment also includes no laves phase.
  • the microstructure of the martensitic stainless steel alloys of this invention contains substantially no chi phase, which in an embodiment also includes no chi phase.
  • the microstructure of the martensitic stainless steel alloys of this invention contains substantially no delta ferrite phase, which in an embodiment also includes no delta ferrite phase.
  • the microstructure of the martensitic stainless steel alloys of this invention contains substantially no laves phase, chi phase and delta ferrite phase, which in an embodiment also includes no laves phase, chi phase and delta ferrite phase.
  • N has a large effect on the PREN, and may optionally be included in the claimed stainless steel materials.
  • N is difficult to add in significant amounts in vacuum melted materials.
  • N can also combine with Cr in the alloy microstructure to form chromium nitrides, which can embrittle and sensitize the stainless steel materials by local depletion of chromium within the alloy microstructure, particularly at the alloy surface, where contact with corrosive species is possible, as described herein.
  • N will generally be present in amount of 0.02 weight percent or less, and more particularly about 0.001 to about 0.02 weight percent.
  • the composition of the claimed stainless steel alloys will have a high temperature microstructure that includes austenite. Since both Cr and Mo are ferrite stabilizers, consequently, an austenite former is required to balance the phase diagram and develop a high temperature austenite phase to facilitate a martensitic heat treatment and provide the martensitic microstructure, while also developing a predetermined amount of retained austenite and substantially no delta ferrite, which in an embodiment also includes no delta ferrite. Co was selected to stabilize austenite.
  • Co is present in an amount of about 16.0 to about 20.0 weight percent, and more particularly about 16.5 to about 20.0 weight percent, and even more particularly about 16.5 to about 18.0 weight percent.
  • an austenite stabilizer cobalt provides a sufficiently large austenite phase field for temperature and/or time latitude in the heat treatment process.
  • the effect of Co on the martensite start, M s , temperature is not as pronounced as that of Ni, providing for the use of standard quench and temper heat treatment protocols.
  • Ni is a required constituent and will be present in an amount sufficient to stabilize austenite.
  • Ni is an austenite stabilizer and increases the amount of retained austenite in these alloys.
  • the amount of Ni should be controlled to provide a predetermined amount of a retained austenite phase in the alloy microstructure.
  • the predetermined amount of the retained austenite phase comprises at least about 15 percent by volume of the alloy microstructure.
  • the predetermined amount of retained austenite phase comprises about 15 percent to about 25 percent by volume of the alloy microstructure.
  • the amount of Ni comprises about 1.0 to about 3.0 weight percent, and more particularly, about 1.0 to about 2.0, and yet more particularly about 1.0 to about 1.5 weight percent.
  • the predetermined amount of retained austenite improves the fracture toughness of the claimed alloys.
  • Ni in the amounts described herein also increases the Charpy V-notch toughness of the martensitic stainless steel alloys described herein.
  • C is a required constituent and will be present in an amount sufficient to provide a predetermine hardness and/or a predetermined tensile strength.
  • the amount of C is also selected to avoid the formation of coarse M 23 C 6 carbides. These carbides preferentially nucleate at grain boundaries and cause reduced toughness. Chromium carbides also deplete the matrix surrounding the carbide of chromium, leading to a reduction of corrosion resistance.
  • C is present in an amount less than about 0.05 weight percent.
  • C is present in an amount of about 0.020 to about 0.40 weight percent, and more particularly about 0.20 to about 0.30 weight percent, and even more particularly about 0.025 weight percent.
  • the predetermined hardness is about 30 to about 42 HRC
  • the predetermined ultimate tensile strength (UTS) is about 150 to about 200 ksi.
  • the amount of C may be used together with a low temperature tempering heat treatment, as described herein, to provide a predetermined strength and a predetermined fracture toughness that are sufficient for use as turbine airfoil components, including turbine compressor vanes and blades, and more particularly turbine compressor vanes and blades suitable for use in the first through fifth stages of an industrial gas turbine compressor.
  • a method 100 of making a forged, martensitic, pitting corrosion resistant, stainless steel alloy includes providing 110 a forged preform of a martensitic, pitting corrosion resistant stainless steel alloy comprising, by weight: about 12.0 to about 16.0 percent chromium; greater than 16.0 to about 20.0 percent cobalt, about 6.0 to about 8.0 percent molybdenum, about 1.0 to about 3.0 percent nickel, about 0.020 to about 0.040 percent carbon; and the balance iron and incidental impurities.
  • the stainless steel alloys can be provided in any suitable manner, including being processed by substantially conventional methods.
  • the alloy may be produced by electric furnace melting with argon oxygen decarburization (AOD) ladle refinement, followed by electro-slag remelting (ESR) of the ingots.
  • a suitable forming operation such as various forging methods, may then be employed to produce bar stocks and forging preforms that have a precursor shape of the desired article, including the various articles described herein, such as, for example, turbine compressor airfoils.
  • the method 100 also includes heating 120 the forged preform to a solutionizing temperature for a time sufficient to form a solutionized microstructure.
  • the solutionizing temperature comprises about 2,000 to about 2,100°F and the solutionizing time comprises about 1 to about 3 hours.
  • the method further includes cooling 130 the forged preform and solutionized microstructure to room temperature to form a martensitic microstructure.
  • Any suitable method of cooling may be employed that provides a cooling rate sufficient to promote a martensitic transformation of the alloy microstructure.
  • cooling comprises water, polymer, oil, gas, or air quenching.
  • the method also includes heating 140 the forged preform to a tempering temperature of about 600°F or less for a predetermined tempering time sufficient to form a tempered forged preform comprising a tempered martensitic microstructure. Any suitable heating method and tempering time may be employed. In one embodiment, the predetermined tempering time is about 3 to about 6 hours. In one embodiment, the wherein the tempered forged preform comprises a turbine compressor airfoil preform. Still further, the method includes cooling 150 the tempered forged preform to room temperature. Low tempering temperatures, 600°F or less, are utilized to avoid the formation of the precipitates described herein, particularly the embrittling chi and laves phases.
  • the low temperature tempering also establishes a predetermined maximum operating temperature of these alloys that is less than the tempering temperature, preferably at least about 50 to about 100°F lower than the tempering temperature to avoid subsequent tempering of the martensite and changes to the alloy microstructure. It is desirable to keep as much Cr and Mo as possible in solution to provide corrosion resistance and not have the elements bound in intermetallic compounds or carbides.
  • the martensitic stainless steels alloys disclosed herein have a combination of strength, ductility, and fracture toughness that makes them suitable for use to form various turbine airfoil and other components.
  • the martensitic stainless steel alloys exhibited better pitting corrosion resistance than GTD-450 and GTD-450+ after salt fog exposure for 500 hours in accordance with ASTM G85, and in another embodiment exhibited substantially no pitting corrosion after 500 hours of exposure in accordance with ASTM G85, which may also be described in an embodiment as no pitting corrosion in conjunction with this salt fog exposure.
  • the martensitic stainless steels alloys disclosed herein exhibited substantially no pitting corrosion after 1,000 hours of salt fog exposure in accordance with ASTM B117, which may also be described in an embodiment as no pitting corrosion in conjunction with this salt fog exposure.
  • the martensitic stainless steels alloys have an ultimate tensile strength of about 150 ksi or more, and more particularly about 150 to about 200 ksi.
  • the martensitic stainless steels alloys have an elongation of at least about 14 percent, and more particularly an elongation of about 14 to about 24 percent.
  • the martensitic stainless steels alloys have a tensile reduction in area of at least about 41 percent, and more particularly about 41 to about 49 percent. In yet another embodiment, the martensitic stainless steels alloys have a Charpy V-notch toughness of about 85 to about 95 J.
  • the alloys disclosed herein may be used to form turbine airfoil components, including those used for compressor airfoil components of industrial gas turbines.
  • a typical compressor airfoil in the form of a turbine compressor blade is well known.
  • a compressor blade has a leading edge, a trailing edge, a tip edge and a blade root, such as a dovetailed root that is adapted for detachable attachment to a compressor disk.
  • the span of a blade extends from the tip edge to the blade root.
  • the surface of the blade comprehended within the span constitutes the airfoil surface of the turbine airfoil.
  • the airfoil surface is that portion of the turbine compressor airfoil that is exposed to the flow path of air from the turbine inlet through the compressor section of the turbine into the combustion chamber and other portions of the turbine.
  • alloys disclosed herein are particularly useful for use in turbine compressor airfoils in the form of turbine compressor blades and vanes, they are broadly applicable to all manner of turbine compressor airfoils used in a wide variety of components. These include turbine airfoils associated with turbine compressor vanes and nozzles, shrouds, liners and other turbine compressor airfoils, i.e., turbine components having airfoil surfaces such as diaphragm components, seal components, valve stems, nozzle boxes, nozzle plates, or the like.
  • alloys are useful for gas turbine compressor blades and vanes, they can potentially also be used for the turbine components of industrial steam turbines, including compressor blades and vanes, steam turbine buckets and other steam turbine airfoil components, oil and gas machinery components, as well as other applications requiring high tensile strength, fracture toughness and resistance to pitting corrosion so long as the operating temperature range of the components is compatible with the predetermined maximum operating temperature of the alloys as described herein.
  • alloy compositions described herein specifically discloses and includes the embodiments wherein the alloy compositions "consist essentially of” the named components (i.e., contain the named components and no other components that significantly adversely affect the basic and novel features disclosed), and embodiments wherein the alloy compositions "consist of” the named components (i.e., contain only the named components except for contaminants which are naturally and inevitably present in each of the named components).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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US14/632,159 US20160251737A1 (en) 2015-02-26 2015-02-26 Corrosion pitting resistant martensitic stainless steel

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WO2022192839A1 (en) * 2021-03-09 2022-09-15 General Electric Company Corrosion pitting resistant martensitic stainless steel and method for making same

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EP3533897A1 (de) * 2018-02-28 2019-09-04 Siemens Aktiengesellschaft Verbesserungen im zusammenhang mit metalllegierungskomponenten und deren herstellung
WO2019166244A1 (en) * 2018-02-28 2019-09-06 Siemens Aktiengesellschaft Improvements relating to the metal alloy components and their manufacture
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US11697857B2 (en) 2021-03-09 2023-07-11 General Electric Company Corrosion pitting resistant martensitic stainless steel and method for making same

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JP6994817B2 (ja) 2022-01-14
US20160251737A1 (en) 2016-09-01
JP2016166409A (ja) 2016-09-15

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