WO2015197751A1 - Élément constitutif d'une turbomachine, turbomachine et leur procédé de fabrication - Google Patents

Élément constitutif d'une turbomachine, turbomachine et leur procédé de fabrication Download PDF

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Publication number
WO2015197751A1
WO2015197751A1 PCT/EP2015/064350 EP2015064350W WO2015197751A1 WO 2015197751 A1 WO2015197751 A1 WO 2015197751A1 EP 2015064350 W EP2015064350 W EP 2015064350W WO 2015197751 A1 WO2015197751 A1 WO 2015197751A1
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alloy
impurities
component
ppm
temperature
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Filippo Cappuccini
Marco Romanelli
Domenico DI PIETRO
Massimiliano BUCCIONI
Emanuele Pietrangeli
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Nuovo Pignone SRL
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Nuovo Pignone SRL
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Priority to EP15733673.6A priority Critical patent/EP3161174B1/fr
Priority to CN201580034945.8A priority patent/CN106715008A/zh
Priority to JP2016574276A priority patent/JP6767883B2/ja
Publication of WO2015197751A1 publication Critical patent/WO2015197751A1/fr
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • 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
    • 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
    • C22C33/00—Making ferrous alloys
    • C22C33/02—Making ferrous alloys by powder metallurgy
    • C22C33/0257—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements
    • C22C33/0278—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5%
    • C22C33/0285—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5% with Cr, Co, or Ni having a minimum content higher than 5%
    • 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
    • C22C38/004—Very low carbon steels, i.e. having a carbon content of less than 0,01%
    • 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
    • C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
    • 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
    • C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
    • 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
    • C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
    • 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
    • C22C38/42—Ferrous alloys, e.g. steel alloys containing chromium with nickel with copper
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/02—Compacting only
    • B22F3/04—Compacting only by applying fluid pressure, e.g. by cold isostatic pressing [CIP]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • B22F3/15—Hot isostatic pressing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
    • B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F9/00—Making metallic powder or suspensions thereof
    • B22F9/02—Making metallic powder or suspensions thereof using physical processes
    • B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
    • B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying

Definitions

  • Embodiments of the subject matter disclosed herein relate in general to components for turbomachines and to turbomachines for "Oil & Gas” applications.
  • Some embodiments relate to (rotary) centrifugal compressors or pumps, as well as their components, operating in the field of production and treatment of oil and gas containing e.g . hydrocarbon plus hydrogen sulfide, carbon dioxide, with or without other contaminants. These materials are referred as "sour gas".
  • Such apparatuses have at least one component made of a high corrosion resistant alloy, capable of resisting to corrosion better than state of art martensitic stainless steels and behaving similarly to premium nickel base superalloys.
  • Some embodiments relate to (rotary) gas turbines or steam turbines, as well as their components.
  • Such apparatuses have at least one component made of a high mechanical resistant alloy, capable of resisting to fatigue and/or creep better than state of art materials.
  • a compressor is a machine capable of raising the pressure of a compressible fluid (gas) through the use of mechanical energy.
  • centrifugal compressors the compression of the fluid is carried out by one or more impellers assembled on a shaft with a rotating motion inside one or more stator parts (diaphragm) stacked together by bolts.
  • the described assembly is normally called bundle.
  • the fluid to be compressed is drawn into the bundle through one or more intake ducts, whereas the compressed fluid is expelled from the bundle towards one or more delivery ducts.
  • centrifugal compressors are actuated by electric motors or else by internal combustion engines, through a coupl ing for transmitting the motion .
  • Centrifugal compressors that operate in sour gas fields are subject to different type of interaction with the environment (corrosion) that can cause loss of performance and premature failure of compressor components.
  • the sour service is characterized by hydrocarbons with wet hydrogen sulph ide (H 2 S) where the pH 2 S is higher than 0.0030 bar. This value is val id for carbon and low alloy steels.
  • NACE MR0175/ISO 1 51 56-1 doesn't define a minimum pH 2 S l imit for corrosion resistant alloys (CRAs), because this limit is a function also of acidity of the solution (pH) and the values can be lower than the one defined for carbon and low alloy steels.
  • CRAs corrosion resistant alloys
  • wet gas that acts as electrolyte for electrochemical process.
  • the mechan ism involves the d iffusion in the metal of hydrogen atoms generated by corrosion .
  • Contam inants such as hal ides, arsen ic (As), antimony (Sb) and cyan ides (CN " ) act as catalyst, increasing the concentration of hydrogen atoms on surface and by preventing their recombination in hydrogen molecules making SSC more severe.
  • centrifugal compressor components In general , centrifugal compressor components (impellers, shafts, d iaphragms and bolts) are exposed to tensile stress and wet gas cond itions.
  • any pH and low chlorides are the class of material of choice;
  • any pH and high chlorides nickel based alloys are the class of material of choice;
  • a gas turbine is a type of internal combustion engine. It has an upstream rotating compressor coupled to a downstream turbine, and a combustion chamber in-between .
  • Atmospheric air flows through a compressor is brought to higher pressure in a combustion chamber where it is mixed and burnt with fuel (i .e l iquid or gas ) to increase its enthalpy.
  • Th is high-temperature high- pressure flow enters in an expansion turbine, producing a shaft work output in the process.
  • the turbine shaft work is used to drive the compressor and other devices such as an electric generator that may be coupled to the shaft.
  • This environment is characterized by a combination of high temperature, high stress in steady and cycl ing conditions.
  • Materials for such application shall be designed to withstand creep, low and high cycle fatigue, oxidation and corrosion . This is normally accomplished by high strength steels or nickel base alloys.
  • a component of a turbomachine the component being made of an alloy having a chemical composition consisting of:
  • a process for making the above component comprising at least one of the following steps of: a) melting the chemical composition of claim 1 through vacuum induction melting (VIM), or arc electric furnace; b) refining by Argon Oxygen Decarburization (A.O.D.), Vacuum Induction Degassing and Pouring (V. I .D.P), or Vacuum Oxygen Decarburization (V.O.D.); c) re-melting through electro-slag re-melting (E.S.R.), or vacuum arc re-melting (VAR).
  • turbomachine comprising at least one component as defined in general above.
  • Figure 1 shows a three dimensional space governed by partial pressure of H 2 S (p(H 2 S)), pH (mainly function of CO 2 ), and chlorides (and/or other halides) content;
  • Figure 2 shows a typical cross section of centrifugal compressor
  • FIG. 3 shows a typical cross section of centrifugal pump
  • Figure 4 shows a typical cross section of a steam turbine
  • Figure 5 shows a typical cross section of a gas turbine
  • Figure 6A shows the phase equilibrium vs temperature of the alloy of Example 1 and Figure 6B shows the phase equilibrium vs temperature of the comparative UNS N0771 8;
  • Figure 7A shows the Time Temperature Transformation curves for the alloy of Example 1 and Figure 7B shows the Time Temperature Transformation curves for the comparative UNS N0771 8.
  • room temperature has its ordinary meaning as known to those skilled in the art and may include temperatures within the range of about 1 6°C (60°F) to about 32°C (90°F).
  • the term "mandatory element” refers to an element that is present in the alloy and that, in combination with the other mandatory elements, allows to achieve the above objects.
  • the mandatory elements in the alloy are Iron (Fe), Carbon (C), Silicon (Si), Manganese (Mn), Chromium (Cr), Nickel (Ni), Molybdenum (Mo), Copper (Cu), Aluminium (Al), Titanium (Ti), and Niobium (Nb).
  • the term “optional element” refers to an element that is possibly present in addition to the mandatory elements defining the essential chemical composition of the alloy.
  • the optional elements in the alloy are: Cobalt (Co), and Tungsten (W).
  • Impurity refers to an element not provided in the design of the alloy composition in order to reach the aforesaid objects. However, said element may be present because, depending on the manufacturing process, its presence may be unavoidable.
  • Impurities in the alloy comprise phosphorous (P), Sulphur (S), Boron (B), Bismuth (Bi), Calcium (Ca), Magnesium (Mg), Silver (Ag), Lead (Pb), Nitrogen (N), Tin (Sn), and Oxygen (O).
  • At least one component of a turbomachine is made of a high corrosion high temperature resistant alloy, capable of resisting to corrosion and/or stress at high temperature better than state of art martensitic stainless steels and behaving similarly to premium nickel base superalloys like those complying the requirements of UNS N0771 8 e U NS N00625.
  • Said alloy has a chemical composition consisting of:
  • the above alloy is advantageously a cost effective alloy, which at the same time surprisingly encompasses a reduced amount of expensive alloying elements, such as mainly nickel, but also chromium, molybdenum and titanium, without negatively affecting the mechanical and anticorrosion properties.
  • Said alloy also shows a great resistance to high temperatures and pressures, so that the components made of the same result to be advantageously suitable for turbomachines, particularly centrifugal compressors.
  • Said impurities are P, S, B, Bi, Ca, Mg, Ag, Pb, N , Sn, O or a combination thereof.
  • said impurities are less than 0.5 wt%; more preferably, less than 0.2 wt% .
  • said impurities are P up to 0.025 wt%, S up to 0.01 wt%, B, Bi, Ca, Mg, Ag, Pb, N, Sn, and O.
  • the alloy has high resistance to corrosion at high temperature, in particular in the range of 200-250°C. In other embodiments, the alloy has high resistance to fatigue and/or creep at high temperature, in particular in the range of 400-700°C.
  • the alloy has a chemical composition consisting of:
  • the alloy has a chemical composition consisting of:
  • the alloy has a chemical composition consisting of:
  • the alloy has a chemical composition consisting of: c 0.01 5 wt%
  • the alloy has a grain size finer than plate 3 as per ASTM E1 1 2.
  • the above alloy can be obtained by any casting process. However, it is preferred to obtain said alloy by a process comprising at least one of the following steps of: a) melting the above chemical composition through vacuum induction melting (VIM), or arc electric furnace; b) refining by Argon Oxygen Decarburization (A.O.D.), Vacuum Induction Degassing and Pouring (V. I .D.P), or Vacuum Oxygen Decarburization (V.O.D.); c) re-melting through electro-slag re-melting (E.S.R.), or vacuum arc re-melting (VAR).
  • the alloy resulting from the above described casting processes is subjected to a step d) of homogenization at a high temperature, preferably above 1 1 00° C for at least 6 hours.
  • the alloy resulting from the above described casting processes and subsequent step d) of homogenization heat treatment is further subjected to a step e) of hot or cold plastic deformation through at least one plastic deformation cycle, in order to attain a minimum total reduction ratio of 2: 1 .
  • plastic deformation cycles include forging (open or close die), rolling, extrusion, cold expansion, to produce a raw component shape or more generally a raw shape to be further machined to produce centrifugal compressor, pump, gas and steam turbine, as well as components thereof.
  • the alloy resulting from step e) is then subjected to a step f) of heat treatment to induce solubil ization through at least one heat cycle, preferably at a temperature of 1 020-1 1 50°C, that can be carried out inside furnaces, under air, controlled atmosphere or vacuum, and followed by fast cool ing in l iquid or gas med ia, in order to put and keep in solution the alloying elements (i .e copper, titanium, aluminium, niobium, etc .. ) for optional subsequent heat treatment steps.
  • a step f) of heat treatment to induce solubil ization through at least one heat cycle, preferably at a temperature of 1 020-1 1 50°C, that can be carried out inside furnaces, under air, controlled atmosphere or vacuum, and followed by fast cool ing in l iquid or gas med ia, in order to put and keep in solution the alloying elements (i .e copper, titanium, aluminium, niobium, etc .. ) for optional
  • said step f) of heat treatment is followed by a step g) of an ageing treatment.
  • said step g) of an ageing treatment comprises the following sub-steps: g-1 ) heating the alloy to a temperature of 71 0-780°C for 4-8 h; g-2) cooling at a cooling rate of 40-60°C/h down to a temperature of 61 0-670°C; g-3) keeping the alloy to a temperature of 61 0-670°C for at least 6 h, and g-4) letting the alloy to cool at room temperature in air.
  • said step g) of an ageing treatment comprises the following sub-steps: g-1 ') heating the alloy to a temperature of 780-820°C for 2-8 h; and g-2') letting the alloy to cool at room temperature in air.
  • the alloy advantageously shows the following properties: - superior anticorrosion characteristics in terms of general and local ized corrosion, threshold stress in solution A method A as per NACE MR0175, higher Stress Corrosion Cracking (SCC) resistance, higher Chloride Stress Corrosion Cracking (CSCC), Sulphide Stress Cracking (SSC), Galvanically-induced Hydrogen Stress Cracking (GHSC);
  • the alloy is further atomized to produce powder and then treated by powder metallurgy.
  • powder metallurgy it is meant that said powder is consolidated by Cold Isostatic Pressing (CIP), by Metal Injection Moulding (MIM), Sintering, Hot Isostatic Pressing (H IP), or fabricated by MIM and exposed to a H IP process.
  • CIP Cold Isostatic Pressing
  • MIM Metal Injection Moulding
  • H IP Hot Isostatic Pressing
  • powders are fed into a die, compacted to a desired shape.
  • the pressed powder is then sintered or hipped in a controlled atmosphere furnace at room or high pressure to produce metallurgical bonds among powder particles.
  • Optional post- sintering operations such as isothermal forging, infiltration, finish machining or surface treatment, may then be applied to complete the component.
  • Figures 2, 3, 4 and 5 show different turbomachines where one or more components as set out above may be used .
  • Figure 2 shows a typical cross section of centrifugal compressor
  • Figure 3 shows a typical cross section of centrifugal pump
  • Figure 4 shows a typical cross section of a steam turbine
  • Figure 5 shows a typical cross section of a gas turbine. Thanks to its high resistance to corrosion (even at high temperature) and/or to its high resistance to fatigue and/or creep, the component is very useful, in particular it is very useful for components that get in touch with the working fluid of the turbomachine.
  • the above chemical composition was melted through vacuum induction melting (VIM), refined by Argon Oxygen Decarburization (A.O.D.), and re-melted re-melting through electro-slag re-melting (E.S.R.).
  • VIM vacuum induction melting
  • A.O.D. Argon Oxygen Decarburization
  • E.S.R. electro-slag re-melting
  • the resulting alloy was homogenized at a temperature above 1 1 00° C for at least 6 hours.
  • the alloy was then subjected to two cycles of hot plastic deformation . Subsequently, the alloy was subjected to a heat treatment to induce solubilization at a temperature of 1 020-1 1 50°C, followed by fast cooling in liquid or gas media.
  • the resulting alloy has been tested to assess mechanical and anticorrosion properties.
  • the results have been compared to a known Martensitic Stainless Steel (shortly 'Martensitic SS') in the following Table 1 .
  • Martensitic Stainless steels is a category of stainless steels having a microstructure mainly composed by tempered Martensite. Matertensite is formed by a rapid cooling of austenite phase which is achieved by a quenching heat treatment.
  • Traditional martensitic steels have a high carbon content, in the 0.08-1 .% range, a Chromium in the 1 2-1 7% range.
  • Their main characteristic compared other stainless steel classes is the high strength and fair corrosion resistance. Table 1 .
  • the alloying elements' weight percent is tailored to avoid or minimizing topologically closed packed phases (TCP). Excessive quantities of Cr, Mo, W would promote the precipitation of intermetall ic phases which are rich in these elements.
  • TCP phases have chemical formulae A x B y .
  • the ⁇ phase is based on the ideal stoichiometry A 6 B 7 and has a rhombohedral cell containing 1 3 atoms, such as W 6 Co 7 and Mo6Co 7 .
  • the ⁇ phase is based upon the stoich iometry A 2 B and has a tetragonal cell containing 30 atoms, such as Cr 2 Ru, Cr 6 i C039 and Re67Mo33-
  • the P phase for example, Cri 8 Mo 4 2N i 0 is primitive orthorhombic, containing 56 atoms per cell .
  • this alloy has a hot forming range between 900°-1 200°C, thus reducing the risk of failure during production and cycle time.
  • the alloy has a combination of chemical elements so as to provide secondary phases hardening such as to provide a minimum yield strength of 750 Mpa with a max hardness of 34 HRC thus enhancing stress corrosion properties.
  • the reduced hardness level results in a better machining if compared with premium nickel based alloys like UNS N0771 8. This level of hardness allows the turbomachinery components to be machined in aged conditions resulting in an optimization of manufacturing cycle if compared with premium nickel based alloys like UNS N0771 8.
  • This alloy is designed to be easy welded by common arc welding processes (SMAW and GTAW) with homologous or different nickel base filler materials like UNS N06625, U NS N07725, or UNS N09925.
  • SMAW and GTAW common arc welding processes

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  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Heat Treatment Of Articles (AREA)
  • Treatment Of Steel In Its Molten State (AREA)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)
  • Powder Metallurgy (AREA)
  • Heat Treatment Of Steel (AREA)

Abstract

L'invention concerne des turbomachines, ainsi que leurs éléments constitutifs, dans le domaine de la production et du traitement de pétrole et de gaz contenant, par exemple, un hydrocarbure plus du sulfure d'hydrogène et du dioxyde de carbone, avec ou sans autres contaminants. Lesdits éléments constitutifs sont constitués d'un alliage extrêmement résistant aux températures élevées et à la corrosion, pouvant mieux résister à la corrosion et/ou à une contrainte à haute température que les aciers inoxydables martensitiques de l'état de la technique et se comportant comme des superalliages à base de nickel de première qualité.
PCT/EP2015/064350 2014-06-27 2015-06-25 Élément constitutif d'une turbomachine, turbomachine et leur procédé de fabrication Ceased WO2015197751A1 (fr)

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EP15733673.6A EP3161174B1 (fr) 2014-06-27 2015-06-25 Élément constitutif d'une turbomachine, turbomachine et leur procédé de fabrication
CN201580034945.8A CN106715008A (zh) 2014-06-27 2015-06-25 涡轮机的部件、涡轮机和用于制备涡轮机的方法
JP2016574276A JP6767883B2 (ja) 2014-06-27 2015-06-25 ターボマシンの構成要素、ターボマシン、およびその作製方法

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ITCO20140021 2014-06-27

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ITUA20163944A1 (it) * 2016-05-30 2017-11-30 Nuovo Pignone Tecnologie Srl Process for making a component of a turbomachine, a component obtainable thereby and turbomachine comprising the same / Processo per ottenere un componente di turbomacchina, componente da esso ottenibile e turbomacchina che lo comprende
CN114038642A (zh) * 2021-10-12 2022-02-11 泉州天智合金材料科技有限公司 一种Fe-Co软磁合金吸波粉末及其制备方法
US20230151459A1 (en) * 2018-05-11 2023-05-18 Etikrom A.S. Nickel-based alloy embodiments and method of making and using the same

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CN107119230A (zh) * 2017-06-26 2017-09-01 扬中市第蝶阀厂有限公司 一种调节阀阀体材料
JP2020533490A (ja) * 2017-09-07 2020-11-19 スズキ ガルフィタン アクチエボラグ 冷間引抜きワイヤを製造するための方法
IT201800004541A1 (it) * 2018-04-16 2019-10-16 Procedimento per la produzione di una superlega e superlega ottenuta con il procedimento
CN112430782B (zh) * 2020-10-23 2022-07-05 中国石油天然气集团有限公司 一种地热井用套管及其制造方法
CN116377314B (zh) * 2023-06-05 2023-10-27 成都先进金属材料产业技术研究院股份有限公司 一种燃气轮机用马氏体耐热钢及其冶炼方法

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ITUA20163944A1 (it) * 2016-05-30 2017-11-30 Nuovo Pignone Tecnologie Srl Process for making a component of a turbomachine, a component obtainable thereby and turbomachine comprising the same / Processo per ottenere un componente di turbomacchina, componente da esso ottenibile e turbomacchina che lo comprende
WO2017207414A1 (fr) * 2016-05-30 2017-12-07 Nuovo Pignone Tecnologie Srl Procédé de fabrication d'un composant d'une turbomachine, composant pouvant être obtenu par ce procédé et turbomachine comprenant celui-ci
CN109195733A (zh) * 2016-05-30 2019-01-11 诺沃皮尼奥内技术股份有限公司 用于制造涡轮机部件的方法、通过此方法可获得的部件以及包括所述部件的涡轮机
JP2019523822A (ja) * 2016-05-30 2019-08-29 ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｔｅｃｎｏｌｏｇｉｅ Ｓ．Ｒ．Ｌ． ターボ機械部品の製造方法、それによって得られる部品およびそれを備えたターボ機械
RU2730916C2 (ru) * 2016-05-30 2020-08-26 Нуово Пиньоне Текнолоджи Срл Способ получения компонента турбомашины, компонент, полученный этим способом, и турбомашина, содержащая этот компонент
JP7153567B2 (ja) 2016-05-30 2022-10-14 ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータ ターボ機械部品の製造方法、それによって得られる部品およびそれを備えたターボ機械
US11780010B2 (en) 2016-05-30 2023-10-10 Nuovo Pignone Technologie Srl Process for making a component of a turbomachine, a component obtainable thereby and turbomachine comprising the same
US20230151459A1 (en) * 2018-05-11 2023-05-18 Etikrom A.S. Nickel-based alloy embodiments and method of making and using the same
CN114038642A (zh) * 2021-10-12 2022-02-11 泉州天智合金材料科技有限公司 一种Fe-Co软磁合金吸波粉末及其制备方法

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CN106715008A (zh) 2017-05-24
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EP3161174A1 (fr) 2017-05-03
JP2017525842A (ja) 2017-09-07

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