WO2013153020A2 - Method for preventing corrosion and component obtained by means of such - Google Patents

Method for preventing corrosion and component obtained by means of such Download PDF

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Publication number
WO2013153020A2
WO2013153020A2 PCT/EP2013/057287 EP2013057287W WO2013153020A2 WO 2013153020 A2 WO2013153020 A2 WO 2013153020A2 EP 2013057287 W EP2013057287 W EP 2013057287W WO 2013153020 A2 WO2013153020 A2 WO 2013153020A2
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WIPO (PCT)
Prior art keywords
layer
coating
nickel
μιη
thickness
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2013/057287
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French (fr)
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WO2013153020A3 (en
Inventor
Massimo Giannozzi
Riccardo Paoletti
Marco Romanelli
Marco Anselmi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nuovo Pignone SRL
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Nuovo Pignone SRL
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nuovo Pignone SRL filed Critical Nuovo Pignone SRL
Priority to CA2869436A priority Critical patent/CA2869436C/en
Priority to JP2015504918A priority patent/JP6163537B2/en
Priority to CN201380019338.5A priority patent/CN104379817B/en
Priority to AU2013246985A priority patent/AU2013246985B2/en
Priority to KR1020147030544A priority patent/KR102116331B1/en
Priority to MX2014012322A priority patent/MX2014012322A/en
Priority to EP13715669.1A priority patent/EP2836626B1/en
Priority to BR112014024992A priority patent/BR112014024992B8/en
Priority to US14/391,708 priority patent/US10161413B2/en
Publication of WO2013153020A2 publication Critical patent/WO2013153020A2/en
Publication of WO2013153020A3 publication Critical patent/WO2013153020A3/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
    • C23C18/1601—Process or apparatus
    • C23C18/1633—Process of electroless plating
    • C23C18/1646—Characteristics of the product obtained
    • C23C18/165—Multilayered product
    • C23C18/1653—Two or more layers with at least one layer obtained by electroless plating and one layer obtained by electroplating
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
    • C23C18/1601—Process or apparatus
    • C23C18/1633—Process of electroless plating
    • C23C18/1635—Composition of the substrate
    • C23C18/1637—Composition of the substrate metallic substrate
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
    • C23C18/1601—Process or apparatus
    • C23C18/1633—Process of electroless plating
    • C23C18/1689—After-treatment
    • C23C18/1692—Heat-treatment
    • C23C18/1698—Control of temperature
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D5/00—Electroplating characterised by the process; Pretreatment or after-treatment of workpieces
    • C25D5/10—Electroplating with more than one layer of the same or of different metals
    • C25D5/12—Electroplating with more than one layer of the same or of different metals at least one layer being of nickel or chromium
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D5/00—Electroplating characterised by the process; Pretreatment or after-treatment of workpieces
    • C25D5/60—Electroplating characterised by the structure or texture of the layers
    • C25D5/623—Porosity of the layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F04D25/0686—Units comprising pumps and their driving means the pump being electrically driven specially adapted for submerged use
    • 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
    • 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
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
    • C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
    • C23C18/48—Coating with alloys
    • C23C18/50—Coating with alloys with alloys based on iron, cobalt or nickel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/16—Other metals not provided for in groups F05D2300/11 - F05D2300/15
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the present invention relates to a method for preventing corrosion in a subsea or onshore or offshore component.
  • the method of the present invention can be advantageously used for preventing corrosion in a component of a subsea or onshore or offshore turbo-machine.
  • materials like carbon steel, low-alloy steel and stainless steel are normally used when building components which operate in subsea or onshore or offshore environments. If such environments comprise wet carbon dioxide (C0 2 ), carbon steel and low-alloy steel will be affected by corrosion damages. Moreover, if such environments comprise chlorides, stainless steel will be affected by pitting corrosion damages.
  • the present invention accomplishes such an object by providing a method for preventing corrosion in a component of a turbo-machine having a metal substrate made of carbon steel, low alloy steel or stainless steel, wherein the method includes:
  • a first deposition step of depositing a first metallic layer on said substrate by electroplating - a second deposition step of depositing at least a second layer of a nickel alloy on said first layer by electroless plating;
  • thermal treatment being applied at a temperature and for a time depending on the overall thickness of said layers, the value of said temperature being directly proportional to said thickness, the value of said time being inversely proportional to said temperature.
  • the method further includes a third deposition step of depositing a third metallic layer on said second layer by electroplating and a fourth deposition step of depositing a fourth layer of said nickel alloy on said third layer by electroless plating.
  • the value of the overall thickness of said layers is between 70 ⁇ and 300 ⁇ .
  • the solution of the present invention by providing a multi-layer coating consisting of a nickel-based coating and having the above specified thickness, allows an efficient protection of the core metal substrate.
  • the electroless nickel plating process provide cost saving by providing an anti- corrosion coating less expensive than stainless steel and more costly alloys (for example nickel-based alloys like Inconel 625, Inconel 718) and by permitting the use of a less expensive material in the core metal substrate, for example carbon or low alloy steel.
  • the electroless plating process can be easily applied to components of any shape, in particular of complex shape.
  • the present invention accomplishes the above object also by providing a turbo- machine including a component comprising a metal substrate made of carbon steel, low alloy steel or stainless steel, and a coating including nickel on said substrate, said coating comprising at least a first metallic layer deposited by electroplating and at least a second layer of a nickel alloy deposited by electro less plating, a third metallic layer deposited by electroplating and a fourth layer of a nickel alloy deposited by electro less plating, the thickness of said coating being between 70 ⁇ and 300 ⁇ , said coating having a hardness value between 600 HVioo and 650 HVioo and a ductility value between 1.000% and 1.025%.
  • the turbomachine of the present invention consists in a motor-compressor comprising a casing having a coating on the internal and/or external surfaces obtained with the method of the present invention.
  • the present invention accomplishes the above object also by providing a plant for extracting a liquid and/or gaseous hydrocarbon mixture including a wellhead, a pipeline and a turbo-machine as previously described, wherein said pipeline directly connects said turbo-machine to said wellhead.
  • the anti-corrosive properties of the turbo-machine according to the present invention permit to avoid the use of scrubbers and filter systems upstream the turbo-machine, for preventing corrosive substances from reaching the turbo -machine.
  • FIG. 2 is an assonometric view of a component of a subsea turbomachine according to the present invention
  • - Figure 3 is a section view of the component of figure 2;
  • FIG. 4 is a section view of a component of a centrifugal turbo-compressor for onshore or offshore applications, according to the present invention
  • - Figure 5 is an enlarged view of the detail V in figure 3 and 4;
  • FIG. 6 is an enlarged view of the detail V in figure 3 and 4, corresponding to a different embodiment of the present invention
  • FIG. 7a is a schematic view of a known-in-the-art plant for extracting gas from a reservoir
  • FIG. 7b is a schematic view of a plant for extracting gas from a reservoir, including a component of a turbomachine according to the present invention.
  • a method for preventing corrosion in a component 1 of a turbo-machine 201 is overall indicated with 100.
  • the component 1 has a metal substrate 5 made of carbon steel, low alloy steel or stainless steel.
  • the subsea component 1 is the casing of a subsea compressor.
  • the method of the present invention is applied to the casing of a motor-compressor operating onshore or offshore.
  • the method of the present invention can be successfully applied to other components for subsea applications or operating in other type of humid environment, particularly when carbon dioxide (C0 2 ) and/or hydrogen sulphide (H 2 S) and/or chlorides are present, provided that the method 100 comprises at least a first deposition step 110, a second deposition step 120 and a final thermal treatment step 140, as detailed in the following.
  • the first deposition step 110 consists in depositing a first layer 2a of metallic nickel on the metal substrate 5 by electroplating.
  • the first layer 2a is known in the art as nickel strike and has a thickness comprised between 1 to 10 ⁇ , providing activation for the following second step 120
  • the second deposition step 120 consists in depositing a second layer 2b of a nickel alloy on the first layer 2a by electroless nickel plating (also known as ENP).
  • ENP electroless nickel plating
  • the nickel alloy used in the second deposition step 120 of the method 100 consists of a nickel-phosphorous alloy.
  • the nickel- phosphorous alloy used in the second deposition step 120 includes 9 to 11 % of phosphorous.
  • different nickel alloys are used, for example a nickel and boron alloy.
  • the second deposition step 120 includes a first phase of depositing a first portion 20b of the second layer 2b and a second phase of depositing a second portion 21b of the second layer 2b.
  • the thickness of the first portion 20b of the second layer 2b is comprised between 10 to 25 ⁇ .
  • the thickness of the second portion 21b of the second layer 2b is equal or greater than the double of the second layer, i.e. equal or greater than 20 ⁇ .
  • the method 100 includes further steps of depositing further layers of the nickel alloy by electroless nickel plating, each layer having a thickness greater than the thickness of the previous one.
  • the method 100 after the second deposition step 120 include a third deposition step 130 of depositing a third nickel layer 2c on the second layer 2b by electroplating and a fourth deposition step 135 of depositing a fourth layer 2d of nickel alloy on the third layer 2c by electroless plating.
  • the third layer 2c is obtained by impulse electroplating and provides adhesion between the second and fourth ENP layers 2b, 2d.
  • the third layer 2c avoids formation of pinholes porosity which often occurs in ENP layers having a thickness of more than 100 ⁇ .
  • the third and fourth deposition steps 130, 135 can be repeated more than one time in order to obtain a multilayer structure wherein each electroless-plating layer is deposited over a respective electroplating nickel layer.
  • the coating 2 may include one or more ENP layers.
  • the coating 2 consists of the first and second layers 2a, 2b, the latter comprising a first and a second portion 20b, 21b, both obtained by electroless nickel plating.
  • the coating 2 consists of the first, second, third and fourth layers 2a, 2b, 2c, 2d.
  • the overall thickness of the coating 2 is between 70 ⁇ and 300 ⁇ .
  • the coating 2 is applied to the inner side of the casing of a subsea motor-compressor.
  • the coating 2 is applied to the inner side of the casing of a motor-compressor for onshore or offshore applications.
  • the coating 2 is applied also on the outer side or on both the inner and the outer sides.
  • the method 100 includes a final thermal treatment step 140 applied by exposing the coating 2 to a heating environment, for example in heat treatment oven, at a temperature T and for a time t.
  • the execution of the thermal treatment step 140 allows to get the desorption of the hydrogen incorporated in the coating during the electroplating process.
  • the layers of the coating 2 are made more resistant, adherent to each other and structurally homogeneous.
  • the values of temperature and time data T,t are comprised between 100° C and 300 ° C and between 2 h and 6 h, respectively.
  • the values of temperature and time depend on the overall thickness of the coating 2, the value of said temperature T being directly proportional to the thickness of the nickel coating 2, the value of said time t being inversely proportional to the thickness of the temperature.
  • the values of temperature T and of time t are dependent on the value of the overall thickness of the nickel coating 2, according to the following table:
  • the above heat treatment allows to reach an hardness value between 600 HVioo and 650 HVioo and a ductility value between 1.000% and 1.025% in the nickel-based coating 2.
  • the hardness of the coating 2 improves resistance to erosion or abrasion from solid particulate which may flow in the turbo-machine 201 , in contact with the coating 2.
  • the best hardness and ductility results are obtained when the thickness of the coating 2 is between 150 ⁇ and 300 ⁇ .
  • more than one final thermal treatment step are applied, provided that the above characteristics are reached in the coating 2.
  • a conventional plant 200a for extracting a liquid and/or gaseous hydrocarbon mixture from a natural reservoir 205 includes a wellhead 202 , a dry or wet scrubber 207 downstream the wellhead 202, a filter 208 downstream the scrubber 207 and a traditional turbo-machine 201a, e.g. a traditional centrifugal compressor or a subsea motor-compressor.
  • the scrubber 207 prevents pollutants and in particular corrosive substances, e.g. carbon dioxide (C0 2 ) and/or hydrogen sulphide (3 ⁇ 4S) and/or chlorides, to reach the turbo-machine 201a.
  • the filter 208 prevents solid particulate to reach the turbo-machine 201a.
  • a plant 200 according to the present invention for extracting the same hydrocarbon mixture from the natural reservoir 205 includes a pipeline 203 and the turbo-machine 201.
  • the pipeline 203 directly connects the turbo-machine 201 of the present invention to the wellhead 202. This means that the anti-corrosive properties of the turbo-machine according to the present invention permit to avoid the use of scrubbers and filter systems upstream the turbo -machine.
  • the present invention allows to reach further advantages.
  • the method above described allows to avoid the presence of through porosity in the coating.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • General Chemical & Material Sciences (AREA)
  • Electrochemistry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Geology (AREA)
  • Mining & Mineral Resources (AREA)
  • Electroplating Methods And Accessories (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Physics & Mathematics (AREA)
  • Environmental & Geological Engineering (AREA)
  • Fluid Mechanics (AREA)
  • General Life Sciences & Earth Sciences (AREA)
  • Geochemistry & Mineralogy (AREA)
  • Chemically Coating (AREA)

Description

METHOD FOR PREVENTING CORROSION AND COMPONENT OBTAINED
BY MEANS OF SUCH
The present invention relates to a method for preventing corrosion in a subsea or onshore or offshore component. The method of the present invention can be advantageously used for preventing corrosion in a component of a subsea or onshore or offshore turbo-machine.
Materials like carbon steel, low-alloy steel and stainless steel are normally used when building components which operate in subsea or onshore or offshore environments. If such environments comprise wet carbon dioxide (C02), carbon steel and low-alloy steel will be affected by corrosion damages. Moreover, if such environments comprise chlorides, stainless steel will be affected by pitting corrosion damages.
It is therefore an object of the present invention to provide an improved manufacturing method for preventing corrosion, which could avoid the above inconveniencies by: - efficiently solving the corrosion problem in most of the humid environments containing aggressive contaminants such as chlorides, C02 and Hydrogen Sulphide (H2S), and at the same time by
- using less costly materials.
It is a further object of the present invention to provide an improved manufacturing method for preventing corrosion on the internal and external surfaces of subsea or onshore or offshore components of complex shape, for example the casing of a motor- compressor.
The present invention accomplishes such an object by providing a method for preventing corrosion in a component of a turbo-machine having a metal substrate made of carbon steel, low alloy steel or stainless steel, wherein the method includes:
- a first deposition step of depositing a first metallic layer on said substrate by electroplating; - a second deposition step of depositing at least a second layer of a nickel alloy on said first layer by electroless plating;
- at least one thermal treatment step after said deposition steps, said thermal treatment being applied at a temperature and for a time depending on the overall thickness of said layers, the value of said temperature being directly proportional to said thickness, the value of said time being inversely proportional to said temperature.
According to a further advantageous feature of the first embodiment, the method further includes a third deposition step of depositing a third metallic layer on said second layer by electroplating and a fourth deposition step of depositing a fourth layer of said nickel alloy on said third layer by electroless plating.
According to a further advantageous feature of the first embodiment, the value of the overall thickness of said layers is between 70 μιη and 300 μιη.
The solution of the present invention, by providing a multi-layer coating consisting of a nickel-based coating and having the above specified thickness, allows an efficient protection of the core metal substrate. The thermal treatment included in the method allow to achieve a resistant and structurally homogeneous coating having optimum values of ductility (□□= 1.000% to (□□= 1.025%) and hardness (HVi00=600 to HVioo=650).
The electroless nickel plating process provide cost saving by providing an anti- corrosion coating less expensive than stainless steel and more costly alloys (for example nickel-based alloys like Inconel 625, Inconel 718) and by permitting the use of a less expensive material in the core metal substrate, for example carbon or low alloy steel.
The electroless plating process can be easily applied to components of any shape, in particular of complex shape.
The present invention accomplishes the above object also by providing a turbo- machine including a component comprising a metal substrate made of carbon steel, low alloy steel or stainless steel, and a coating including nickel on said substrate, said coating comprising at least a first metallic layer deposited by electroplating and at least a second layer of a nickel alloy deposited by electro less plating, a third metallic layer deposited by electroplating and a fourth layer of a nickel alloy deposited by electro less plating, the thickness of said coating being between 70 μιη and 300 μιη, said coating having a hardness value between 600 HVioo and 650 HVioo and a ductility value between 1.000% and 1.025%.
Particularly, albeit not exclusively, the turbomachine of the present invention consists in a motor-compressor comprising a casing having a coating on the internal and/or external surfaces obtained with the method of the present invention. Further, the present invention accomplishes the above object also by providing a plant for extracting a liquid and/or gaseous hydrocarbon mixture including a wellhead, a pipeline and a turbo-machine as previously described, wherein said pipeline directly connects said turbo-machine to said wellhead. The anti-corrosive properties of the turbo-machine according to the present invention permit to avoid the use of scrubbers and filter systems upstream the turbo-machine, for preventing corrosive substances from reaching the turbo -machine.
Other object feature and advantages of the present invention will become evident from the following description of the embodiments of the invention taken in conjunction with the following drawings, wherein: - Figures la- lb are two block diagrams schematically showing a first embodiment and a second embodiment, respectively, of a method for preventing corrosion according to the present invention;
- Figure 2 is an assonometric view of a component of a subsea turbomachine according to the present invention; - Figure 3 is a section view of the component of figure 2;
- Figure 4 is a section view of a component of a centrifugal turbo-compressor for onshore or offshore applications, according to the present invention; - Figure 5 is an enlarged view of the detail V in figure 3 and 4;
- Figure 6 is an enlarged view of the detail V in figure 3 and 4, corresponding to a different embodiment of the present invention;
- Figure 7a is a schematic view of a known-in-the-art plant for extracting gas from a reservoir;
- Figure 7b is a schematic view of a plant for extracting gas from a reservoir, including a component of a turbomachine according to the present invention.
With reference to the attached figures, a method for preventing corrosion in a component 1 of a turbo-machine 201 is overall indicated with 100. The component 1 has a metal substrate 5 made of carbon steel, low alloy steel or stainless steel.
In the embodiment in figures 2 and 3, the subsea component 1 is the casing of a subsea compressor.
According to the embodiments in figure 4, the method of the present invention is applied to the casing of a motor-compressor operating onshore or offshore. Particularly, albeit not exclusively, the method of the present invention can be successfully applied to other components for subsea applications or operating in other type of humid environment, particularly when carbon dioxide (C02) and/or hydrogen sulphide (H2S) and/or chlorides are present, provided that the method 100 comprises at least a first deposition step 110, a second deposition step 120 and a final thermal treatment step 140, as detailed in the following.
The first deposition step 110 consists in depositing a first layer 2a of metallic nickel on the metal substrate 5 by electroplating.
The first layer 2a is known in the art as nickel strike and has a thickness comprised between 1 to 10 μιη, providing activation for the following second step 120 The second deposition step 120 consists in depositing a second layer 2b of a nickel alloy on the first layer 2a by electroless nickel plating (also known as ENP). According to an embodiment of the present invention, the nickel alloy used in the second deposition step 120 of the method 100 consists of a nickel-phosphorous alloy.
According to a more specific embodiment of the present invention, the nickel- phosphorous alloy used in the second deposition step 120 includes 9 to 11 % of phosphorous.
According to other embodiments of the present invention, different nickel alloys are used, for example a nickel and boron alloy.
According to an embodiment of the present invention (figure la and figure 5), the second deposition step 120 includes a first phase of depositing a first portion 20b of the second layer 2b and a second phase of depositing a second portion 21b of the second layer 2b. The thickness of the first portion 20b of the second layer 2b is comprised between 10 to 25 μιη.
The thickness of the second portion 21b of the second layer 2b is equal or greater than the double of the second layer, i.e. equal or greater than 20 μιη.
According to another embodiment of the present invention, the method 100 includes further steps of depositing further layers of the nickel alloy by electroless nickel plating, each layer having a thickness greater than the thickness of the previous one.
According to another embodiment of the present invention (figure lb and figure 6), the method 100, after the second deposition step 120 include a third deposition step 130 of depositing a third nickel layer 2c on the second layer 2b by electroplating and a fourth deposition step 135 of depositing a fourth layer 2d of nickel alloy on the third layer 2c by electroless plating. The third layer 2c is obtained by impulse electroplating and provides adhesion between the second and fourth ENP layers 2b, 2d. In addition, the third layer 2c avoids formation of pinholes porosity which often occurs in ENP layers having a thickness of more than 100 μιη.
According to another embodiment of the present invention (whose results are not shown), the third and fourth deposition steps 130, 135 can be repeated more than one time in order to obtain a multilayer structure wherein each electroless-plating layer is deposited over a respective electroplating nickel layer.
At the end of the electroless nickel plating, a nickel-based coating 2 on the metal substrate 5 is obtained.
As described above, according to different embodiments of the present invention, the coating 2 may include one or more ENP layers.
In the embodiment of figure 5, the coating 2 consists of the first and second layers 2a, 2b, the latter comprising a first and a second portion 20b, 21b, both obtained by electroless nickel plating.
In the embodiment of figure 6, the coating 2 consists of the first, second, third and fourth layers 2a, 2b, 2c, 2d.
In all cases the overall thickness of the coating 2 is between 70 μιη and 300 μιη.
With reference to figure 2 and 3, the coating 2 is applied to the inner side of the casing of a subsea motor-compressor. With reference to figure 4, the coating 2 is applied to the inner side of the casing of a motor-compressor for onshore or offshore applications.
According to other embodiments of the present invention, the coating 2 is applied also on the outer side or on both the inner and the outer sides.
After the deposition steps 1 10, 120, 130, 135 the method 100 includes a final thermal treatment step 140 applied by exposing the coating 2 to a heating environment, for example in heat treatment oven, at a temperature T and for a time t. The execution of the thermal treatment step 140 allows to get the desorption of the hydrogen incorporated in the coating during the electroplating process. Moreover, through the thermal treatment step 140 the layers of the coating 2, are made more resistant, adherent to each other and structurally homogeneous. The values of temperature and time data T,t are comprised between 100° C and 300 ° C and between 2 h and 6 h, respectively. The values of temperature and time depend on the overall thickness of the coating 2, the value of said temperature T being directly proportional to the thickness of the nickel coating 2, the value of said time t being inversely proportional to the thickness of the temperature.
In one embodiment of the method 100 the values of temperature T and of time t are dependent on the value of the overall thickness of the nickel coating 2, according to the following table:
Figure imgf000009_0001
The above heat treatment allows to reach an hardness value between 600 HVioo and 650 HVioo and a ductility value between 1.000% and 1.025% in the nickel-based coating 2. The hardness of the coating 2 improves resistance to erosion or abrasion from solid particulate which may flow in the turbo-machine 201 , in contact with the coating 2.
The best hardness and ductility results are obtained when the thickness of the coating 2 is between 150 μιη and 300 μιη.
According to other embodiments of the present invention, more than one final thermal treatment step are applied, provided that the above characteristics are reached in the coating 2.
With reference to figure 7a a conventional plant 200a for extracting a liquid and/or gaseous hydrocarbon mixture from a natural reservoir 205 includes a wellhead 202 , a dry or wet scrubber 207 downstream the wellhead 202, a filter 208 downstream the scrubber 207 and a traditional turbo-machine 201a, e.g. a traditional centrifugal compressor or a subsea motor-compressor. The scrubber 207 prevents pollutants and in particular corrosive substances, e.g. carbon dioxide (C02) and/or hydrogen sulphide (¾S) and/or chlorides, to reach the turbo-machine 201a. The filter 208 prevents solid particulate to reach the turbo-machine 201a. With reference to figure 7b, a plant 200 according to the present invention for extracting the same hydrocarbon mixture from the natural reservoir 205 includes a pipeline 203 and the turbo-machine 201. The pipeline 203 directly connects the turbo-machine 201 of the present invention to the wellhead 202. This means that the anti-corrosive properties of the turbo-machine according to the present invention permit to avoid the use of scrubbers and filter systems upstream the turbo -machine.
All the embodiments of the present invention allow to accomplish the object and advantages cited above.
In addition the present invention allows to reach further advantages. In particular, the method above described allows to avoid the presence of through porosity in the coating.
This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other example are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

Claims

1. Method (100) for preventing corrosion in a component (1) of a turbo-machine having a metal substrate (5) made of carbon steel, low alloy steel or stainless steel, wherein the method (100) includes:
- a first deposition step (110) of depositing a first nickel layer (2a) on said substrate (5) by electroplating;
- a second deposition step (120) of depositing at least a second layer (2b) of a nickel alloy on said first layer (2a) by electroless plating;
- at least one thermal treatment (140) step after said deposition steps (110, 120), said thermal treatment (140) being applied at a temperature (T) and for a time (t) depending on the overall thickness of said layers (2a, 2b), the value of said temperature (T) being directly proportional to said thickness, the value of said time (t) being inversely proportional to said temperature (T).
2. The method (100) of claim 1, wherein said method (100) further includes a third deposition step (130) of depositing a third metallic layer (2c) on said second layer (2b) by electroplating and a fourth deposition step (135) of depositing a fourth layer (2d) of said nickel alloy on said third layer (2c) by electroless plating.
3. The method (100) of claim 1 or 2, wherein the value of the overall thickness of said layers (2a, 2b, 2c, 2d) is between 70 μιη and 300 μιη.
4. The method (100) of any preceding claim, wherein said layers (2b, 2d) of said nickel alloy comprise 9 to 11 % of phosphorus.
5. The method (100) of any preceding claim, wherein said thermal treatment is applied at a temperature (T) comprised between 150° C and 300 ° C and for a time (t) comprised between 2 h and 5 h.
6. The method (100) of any preceding claim, wherein said values of temperature (T) and of time (t) are dependent on the value of the overall thickness of said layers (2a, 2b, 2c, 2d) according to the following table: thickness time temperature
150 μηι 2 hours 200°C
120 μηι 3 hours 190°C
100 μηι 4 hours 180°C
7. A motor-compressor casing (1) comprising a metal substrate (5) made of carbon steel, low alloy steel or stainless steel, and a coating (2) including nickel on said substrate (5), said coating (2) comprising at least a first metallic layer (2a) deposited by electroplating and at least a second layer (2b) of a nickel alloy deposited by electroless plating, the thickness of said coating (2) being between 70 μιη and 300 μιη.
8. A turbomachine including a casing according to claim 7.
9. A turbomachine (201) including a component (1) comprising a metal substrate (5) made of carbon steel, low alloy steel or stainless steel, and a coating (2) including nickel on said substrate (5), said coating (2) comprising at least a first metallic layer (2a) deposited by electroplating and at least a second layer (2b) of a nickel alloy deposited by electroless plating, the thickness of said coating (2) being between 70 μιη and 300 μιη.
10. The turbomachine (201) of claim 9, wherein said coating further include a third metallic layer (2c) deposited by electroplating and a fourth layer (2d) of a nickel alloy deposited by electroless plating.
1 1. The turbomachine (201) of claim 9 or 10, wherein said coating (2) has a hardness value between 600 HVioo and 650 HVioo and a ductility value between 1.000% and 1.025%.
12. A plant (200) for extracting a liquid and/or gaseous hydrocarbon mixture including a wellhead (202), a pipeline (203) and a turbo-machine (201) according to one of the claims 8 to 1 1, wherein said pipeline (203) connects said turbo-machine (201) to said wellhead (202).
PCT/EP2013/057287 2012-04-12 2013-04-08 Method for preventing corrosion and component obtained by means of such Ceased WO2013153020A2 (en)

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CN201380019338.5A CN104379817B (en) 2012-04-12 2013-04-08 Method for preventing corrosion and parts obtained by this method
AU2013246985A AU2013246985B2 (en) 2012-04-12 2013-04-08 Method for preventing corrosion and component obtained by means of such
KR1020147030544A KR102116331B1 (en) 2012-04-12 2013-04-08 Method for preventing corrosion and component obtained by means of such
MX2014012322A MX2014012322A (en) 2012-04-12 2013-04-08 Method for preventing corrosion and component obtained by means of such.
EP13715669.1A EP2836626B1 (en) 2012-04-12 2013-04-08 Method for preventing corrosion and component obtained by means of such
BR112014024992A BR112014024992B8 (en) 2012-04-12 2013-04-08 ENGINE AND TURBOMACHINE COMPRESSOR CASING
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