EP2857546A1 - Komponente einer Turbomaschine und Verfahren zum Beschichten einer Turbomaschinenkomponente - Google Patents

Komponente einer Turbomaschine und Verfahren zum Beschichten einer Turbomaschinenkomponente Download PDF

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Publication number
EP2857546A1
EP2857546A1 EP13187123.8A EP13187123A EP2857546A1 EP 2857546 A1 EP2857546 A1 EP 2857546A1 EP 13187123 A EP13187123 A EP 13187123A EP 2857546 A1 EP2857546 A1 EP 2857546A1
Authority
EP
European Patent Office
Prior art keywords
bond coat
region
turbo machine
machine component
bond
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.)
Withdrawn
Application number
EP13187123.8A
Other languages
English (en)
French (fr)
Inventor
Fathi Ahmad
Karsten Klein
Eckart Schumann
Marco Schüler
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP13187123.8A priority Critical patent/EP2857546A1/de
Priority to PCT/EP2014/068700 priority patent/WO2015049086A1/en
Publication of EP2857546A1 publication Critical patent/EP2857546A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • C23C28/022—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 with at least one MCrAlX layer
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying

Definitions

  • the present invention relates to coated turbo machine components and more particularly to a method of coating turbo machine components with bond coats.
  • Turbo machines like gas turbines or steam turbines are required to operate at high temperatures to achieve high efficiency. They operate at temperatures of the order of 900°C or more. However, as operating temperatures increase, certain components of the turbo machine face higher thermal loading and to overcome the harsh effects of high thermal loading the temperature durability of the turbo machine components must correspondingly increase. For example, the blades and the vanes of the turbo machines face more thermal loading as compared to other parts of the turbo machine. Thermal barrier coatings are used to provide insulation for these turbo machine components that operate at very high temperatures.
  • Such thermal barrier coatings typically consist of four layers: the metal substrate, metallic bond coat, thermally grown oxide, and ceramic topcoat.
  • Turbine blades and vanes need the metallic coating as a bond coating or as an overlay coating.
  • This metallic bond coat has a certain lifetime depending on its thickness and on the temperature level during the operation time.
  • bond coats of different qualities and with different properties are available.
  • Turbine parts coated with a low quality bond coat, such as SC2231 must not be operated in high thermal loading conditions as the low quality bond coat cannot withstand such high thermal loads and would chip off or crack as a result of which the coat would not be able to provide the necessary protection to the parts. Therefore a high quality bond coat, such as SC2464, is used under such conditions.
  • a high quality bond coat is more expensive than the low quality bond coat. So, when the high quality bond coat is applied on all parts of the turbo machine, the turbo machine parts become more expensive to manufacture. This increase in the manufacturing cost of the turbo machine parts leads to lower user satisfaction.
  • the object is achieved by providing a method for coating the turbo machine components with different bond coats based on the thermal load distribution on the turbo machine components and the thermal load bearing capacities of the bond coats.
  • the object is achieved by providing a method for coating a turbo machine component according to claim 1.
  • the proposed solution overcomes the issue of chipping off, spallation or damage caused to bond coats at high thermal loaded operations of the turbo machine component, but at the same time the solution also limits the manufacturing cost of the turbo machine component to a reasonable amount by selectively applying high quality and more expensive bond coats to regions with higher thermal loads and low quality and less expensive bond coats to regions with lower thermal loads.
  • a turbo machine component and a method of coating a turbo machine component with bond coats comprises the steps of coating a first region of the turbo machine component with a first bond coat and coating a second region of the turbo machine component with a second bond coat, wherein during operation of the turbo machine component the first region has lower thermal loading than the second region and the first bond coat has a lower thermal load bearing capacity than the second bond coat.
  • the first bond coat can be SC 2231 and the second bond coat can be SC 2464.
  • the invention also discloses an interface zone on the turbo machine component where the first and the second regions interface.
  • the interface zone is first coated with the first bond coat and thereafter coated with the second bond coat such that the two bond coats overlap and form a composite bond coat.
  • the thickness of the composite bond coat in the interface zone matches a thickness of the first bond coat and the second bond coat on either sides of the interface zone.
  • the method for coating a turbo machine component comprises the step of coating a first region of the turbo machine component with a first bond coat and coating a second region of the turbo machine component with a second bond coat, wherein during operation of the turbo machine component the first region has lower thermal loading than the second region, and the first bond coat has a lower thermal load bearing capacity than the second bond coat.
  • the method has several advantageous characteristics.
  • we can achieve the desired performance of the turbo machine components with superior and complete protection of the components from adverse effects of high temperatures and thermal loads and at the same time achieve cost optimization for manufacturing the components.
  • this method of selectively applying high quality bond coat having higher thermal load bearing capacity to higher thermal loaded areas and low quality bond coat having lower thermal load bearing capacity to lower thermal loaded areas we can reduce the powder loss of the high quality more expensive bond coat as more powder loss takes place while applying bond coats to areas like platform region of a blade which has lower thermal loading.
  • the first bond coat is SC 2231 and the second bond coat is SC 2464.
  • These two bond coats together give the optimum protection to the turbo machine components. Moreover, these two bond coats overlap with each other to form a composite bond coat at an interface zone and provide protection to the components from thermal fatigue caused due to frequent rise and fall of temperature levels during operation of the turbo machine component. This prevents the bond coats from cracking due to thermal fatigue.
  • the first region and the second region overlap at an interface zone such that a part of the first region is at a first side of the interface zone and a part of the second region is at a second side of the interface zone, wherein the interface zone is first coated with the first bond coat and subsequently coated with the second bond coat to form a composite bond coat having a thickness.
  • the composite bond coat in the interface zone has a thickness which matches a thickness of the first bond coat at the first side of the interface zone and the second bond coat at the second side of the interface zone.
  • the interface zone experiences more frequent temperature surges and drops and this leads to surface cracking of the bond coat due to thermal fatigue.
  • the advantage of having a composite bond coat on the interface zone in comparison to having a single layer bond coat is that the composite bond coat prevents surface cracking of the bond coat due to thermal fatigue as it provides a dual layer protection to the interface zone.
  • the two bond coats together form a composite bond coat having a higher thermal load bearing capacity and a higher resistance to thermal fatigue. Thus an optimized material combination is achieved at the interface zone.
  • the first region is at a temperature level less than 900°C and the second region is at a temperature level more than or equal to 900°C.
  • the first and the second regions are coated with the first and the second bond coats respectively using a plasma spray process, wherein the first bond coat is provided via a first powder feed line and the second bond coat is provided via a second powder feed line.
  • Plasma spray process will ensure that the bond coats are uniformly spread over the turbo machine surface.
  • the powder feed lines would ensure that there is a continuous supply of the bond coat material for spraying during the plasma spray process.
  • Plasma spray process offers increased durability of the applied bond coats and provides a spallation resistant layer.
  • the first and the second regions are coated with the first and the second bond coats respectively with the help of a first and a second spray gun, wherein the first powder feed line is connected to the first spray gun and the second powder feed line is connected to the second spray gun.
  • a turbo machine component which broadly comprises a surface having at least a first region and a second region, and a first bond coat on the first region and a second bond coat on the second region, wherein during operation of the turbo machine component the first region has lower thermal loading than the second region and the first bond coat has a lower thermal load bearing capacity than the second bond coat.
  • the first bond coat is SC 2231 and the second bond coat is SC 2464. These two bond coats together give the optimum protection to the turbo machine components and at the same time maintain a reasonable manufacturing cost of the turbo machine components.
  • the first region and the second region overlap at an interface zone such that a part of the first region is at a first side of the interface zone and a part of the second region is at a second side of the interface zone.
  • the interface zone has the second bond coat coated over the first bond coat to form a composite bond coat having a thickness matching a thickness of the first bond coat on the first side of the interface zone and the second bond coat on the second side of the interface zone.
  • the interface zone experiences more frequent temperature variations and this leads to surface cracking of the bond coat due to thermal fatigue.
  • the advantage of having a composite bond coat on the interface zone in comparison to having a single layer bond coat is that the composite bond coat prevents surface cracking of the bond coat due to thermal fatigue as it provides a dual layer protection to the interface zone.
  • the two bond coats together form a composite bond coat having a higher thermal load bearing capacity and a higher resistance to thermal fatigue.
  • the turbo machine component is a blade of a rotor of a turbo machine.
  • the first and the second regions are located on an airfoil of the blade.
  • the blades of a turbo machine rotor are impinged with very high temperature gases or fluids during operation of the turbo machine, therefore the bond coating disclosed in accordance with this invention would provide the necessary protection to the blades during their operation.
  • the rotor has an axis of rotation and the airfoil comprises a radial outer portion and a radial inner portion, wherein the radial direction is defined with reference to the axis of rotation of the rotor.
  • the second region is located at least on the radial outer portion of the airfoil. Coating this second region with the high quality bond coat will protect the higher thermally loaded region, i.e. the radial outer portion of the airfoil, from the impact of high temperature gases and fluids thereby preventing spallation of the bond coat.
  • the radial inner portion of the blade experiences lower thermal loading as compared to the radial outer portion of the blade.
  • the first region is located on the radial inner portion of the airfoil, or on a platform of the blade or on both.
  • Both the radial inner section of an airfoil region as well as the platform region of the blade face lesser thermal loading and hence can be coated with a lower quality and less expensive bond coat having lower thermal load bearing capacity thereby reducing the manufacturing cost of the turbo machine components like airfoils and platforms of blades.
  • the turbo machine component is a vane of a stator of a turbo machine.
  • the vanes of a stator also lie in the path of hot gases or fluids during operation of the turbo machine.
  • the differential coating with two different bond coats depending on the thermal loading of the regions on the vanes will ensure that the vanes are adequately protected and at the same time the manufacturing cost of the vanes are optimized.
  • the vane comprises a surface having a length with a first end and a second end, wherein the first end is separated from the second end by the length of the vane.
  • the vane is attached to the stator at the first end, and the first region is located on the surface at a portion adjacent to the first end and the second region is located on the surface at a portion adjacent to the second end. This helps in identifying and differentiating the regions of higher thermal loading from the regions of lower thermal loading on a vane so that based on the thermal load distribution the different bond coats having different thermal load bearing capacities can be applied to the corresponding regions.
  • a turbo machine component coating comprises a first bond coat to coat at least a first region of a turbo machine component and a second bond coat to coat at least a second region of the turbo machine component, wherein during operation of the turbo machine component the first region has lower thermal loading than the second region, and further the first bond coat has a lower thermal load bearing capacity than the second bond coat.
  • the turbo machine component coating is an airfoil coating.
  • the turbo machine component coating is an airfoil coating, comprising a first bond coat to coat at least a first region of the airfoil and a second bond coat to coat at least a second region of the airfoil, wherein when the airfoil is in operation, the first region has lower thermal loading than the second region, wherein the first bond coat has a lower thermal load bearing capacity than the second bond coat.
  • the second region is located at least on a radial outer portion of the airfoil and the first region is located on the radial inner portion of the airfoil and/or on a platform of the blade.
  • Embodiments of the present invention described below relate to a turbo machine component and more specifically to a blade component of a turbo machine. However, the details of the embodiments described in the following can be transferred to a vane component without modifications, that is the terms "blade” or "vane” can be used in conjunction, since they both have the shape of an airfoil.
  • the turbo machine may include a gas turbine, a steam turbine, a turbofan and the like.
  • FIG. 1 is a schematic diagram of an exemplary turbo machine component 1.
  • the turbo machine component 1 broadly comprises a surface 2 having at least a first region 3 and a second region 4.
  • the turbo machine component 1 further comprises a first bond coat 5 on the first region 3 and a second bond coat 6 on the second region 4.
  • the first region 3 has lower thermal loading than the second region 4 and the first bond coat 5 has a lower thermal load bearing capacity than the second bond coat 6.
  • the first region 3 and the second region 4 interface at an interface zone 7.
  • the first region 3 is at a first side 9 of the interface zone 7 and the second region 4 is at a second side 10 of the interface zone 7.
  • the interface zone 7 is first coated with the first bond coat 5 and subsequently coated with the second bond coat 6 to form a composite bond coat 11.
  • the turbo machine component 1 is a blade 12 of a rotor of the turbo machine. This will be explained in more detail with reference to FIG. 3 .
  • Thermal loading on a region means the impact of gases or fluids at very high temperatures on that region.
  • the operating temperatures can be of the order of 900°C.
  • Thermal load bearing capacity here means the ability to bear high thermal loads without breaking down or wearing out.
  • a high thermal load bearing capacity would mean that the bond coat is capable of withstanding high temperatures and thermal loads without leading to spallation, wear and tear or cracking of the bond coats due to the high temperatures during operation.
  • the first region 3 of the turbo machine component 1 reaches a temperature level of less than 900°C and the second region 4 of the turbo machine component 1 crosses or equals a temperature level of 900°C.
  • the first bond coat 5 is a low quality bond coat.
  • the second bond coat 6 is a high quality bond coat.
  • the first bond coat has preferably a chemical composition of 29-31% Ni, 27-29% Cr, 7-8% Al, 0.5-0.7% Y, 0.3-0.7% Si and rest is Co.
  • the second bond coat has preferably a chemical composition of 24-26 Co, 16-18% Cr, 9.5-11% Al, 0.2-0.4% Y, 1.2-1.8% Re and rest is Ni.
  • FIG. 2 a schematic diagram of a cross-section of the interface zone 7 is disclosed when viewed from a side of the blade 12.
  • the first region 3 and the second region 4 interface at an interface zone 7 such that the first region 3 is at a first side 9 of the interface zone 7 and the second region 4 is at a second side 10 of the interface zone 7.
  • the interface zone 7 is first coated with the first bond coat 5 and subsequently coated with the second bond coat 6 to form a composite bond coat 11.
  • the composite bond coat 11 in the interface zone 7 has a thickness which matches a thickness of the first bond coat 5 at the first side 9 of the interface zone 7 and the second bond coat 6 at the second side 10 of the interface zone 7.
  • the bond coats 5, 6 merge over this interface zone 7 to coat the interface zone 7.
  • the interface zone 7 is coated with dual layers of bond coats.
  • the interface zone 7 experiences a wider range of operating temperatures as compared to the adjacent first 3 and the second 4 regions.
  • the first region 3 experiences operating temperature ranges below 900°C and the second region 4 experiences operating temperature ranges more than or equal to 900°C.
  • the interface region 7 invariably has to experience operating temperature ranges faced by both the first 3 and the second 4 regions as it lies adjacent to both the regions.
  • the effect of coating the interface zone 7 with two bond coats 5, 6 is that the bond coats 5, 6 together form a composite bond coat 11 which is capable of protecting the interface zone 7 from thermal fatigue caused due to the wide range of operating temperatures.
  • the individual properties of each layer of bond coats 5, 6 will also be retained.
  • the thickness of the composite bond coat 11 matches the thickness of the bond coats at the adjacent first 3 and the second 4 regions so that there is no protrusion on the surface of the turbo machine component 1 at the interface region 7. Thus, the flow of hot fluid or gas during operation of the turbo machine is not disturbed.
  • Figure 3 shows the interface zone when seen from the top, i.e. in a direction perpendicular to the surface 2 of the turbo machine component 1 and the blade, respectively.
  • the composite bond coat 11 covers the interface zone 7, whereas the first region 3 is covered by the first bond coat 5 and the second region 4 is covered by the second bond coat 6.
  • the first 3 and the second regions 4 are located on respective first 9 and second sides 10 of the interface zone 7.
  • FIG. 4 shows a schematic diagram of a rotor 13 of a turbo machine.
  • the rotor 13 has an axis of rotation 14 and an axial direction is defined with reference to the axis of rotation 14.
  • the turbo machine component 1 is a blade 12 of the rotor 13 of the turbo machine.
  • the blade 12 comprises an airfoil 26, a platform 17, and a root portion (not shown).
  • the blades 12 of a turbo machine rotor 13 function by rotating in the path way of hot fluids or gases.
  • the blades 12 receive very high impact of hot fluids or gases when the hot fluids or gases impinge on the blades 12. Therefore the bond coatings 5, 6 disclosed in accordance with this invention and explained with reference to FIG. 1 and FIG. 3 would provide the necessary protection to the blades 12 during their operation.
  • the first region 3 is coated with the first bond coat 5 and the second region 4 is coated with the second bond coat 6, wherein both the first as well as the second regions lie on the airfoil 26.
  • the airfoil 26 is covered with the second bond coat 6 and the platform 17 is covered with the first bond coat 5.
  • the airfoil 26 comprises a radial outer portion 15 and a radial inner portion 16.
  • the second region 4 with the second bond coat 6 is located at least on the radial outer portion 15 of the airfoil 26 and the first region 4 with the first bond coat 6 is located at least on the radial inner portion 16 of the airfoil 26.
  • the second region 4 can be the radial outer portion 15 of the airfoil 26 and the first region 3 can be the radial inner portion 16 of the airfoil 26.
  • the second region 4 can be a part of the radial outer portion 15 of the airfoil 26 and the first region 3 can extend from the radial inner portion 16 of the airfoil 26 to a part of the radial outer portion 15 of the airfoil 26 which is not a part of the second region 4.
  • the second region 4 can be both the radial outer portion 15 of the airfoil 26 and the radial inner portion 16 of the airfoil 26.
  • the first region 3 is located on the radial inner portion 16 of the airfoil 12 or on a platform 17 of the blade 12, especially on a radially outer surface of the platform 17. In another embodiment the first region 3 is located both on the radial inner portion 16 of the airfoil 12 and on the platform 17 of the blade 12.
  • FIG. 5 a schematic diagram of a vane 18 of a turbo machine is depicted. As can be seen from the diagram, only one end of the vane 18 is attached to a stator 21 of the turbo machine and the other end is free.
  • Figure 6 shows a schematic diagram of a vane 18 of a turbo machine where the vane 18 is attached to the stator 21 turbo machine at both ends of the vane 18.
  • the bond coat arrangement as disclosed in this invention can also be used for coating vanes of a turbo machine.
  • the vanes also experience high thermal loading during the operation of the turbo machine, like the blades of the rotor.
  • the vane 18 essentially comprises a surface 2 having two ends, a first end 19 and a second end 20 separated from each other by a length of the vane 18 in the radial direction.
  • the vane 18 is attached to the stator 21 at the first end 19, and the first region 3 with the first bond coat 5 is located on the surface 2 at a portion adjacent to the first end 19 and the second region 4 with the second bond coat 6 is located on the surface 2 at a portion adjacent to the second end 19.
  • an interface region (not shown in FIG. 5 and FIG. 6 ) can be located between the first and second region.
  • the bond coats 5, 6 may be applied using any suitable techniques known in the art.
  • the bond coats are applied by a plasma spray process.
  • the bond coats are supplied through powder feed lines to respective spray guns for spraying on desired regions.
  • the first 3 and the second 4 regions are coated with the first 5 and the second 6 bond coats respectively using a plasma spray process, wherein the first bond coat 5 is provided via a first powder feed line 22 and the second bond coat 6 is provided via a second powder feed line 23.
  • the spray of bond coats is ejected from spray guns.
  • the first powder feed line 22 is connected to the first spray gun 24 and the second powder feed line 23 is connected to the second spray gun 25.
  • the first 3 and the second 4 regions are coated with the first 5 and the second 6 bond coats respectively using the first 24 and the second 25 spray gun.
  • the second bond coat 6 has higher thermal load bearing capacity than the first bond coat 5 therefore the air plasma spray (APS) spallation time of the second bond coat 6 is longer than that of the first bond coat 5.
  • the bond coat with the relatively longer APS spallation time, that is the second bond coat 6 is applied after the interface zone 7 is first coated with the first bond coat 5, which has a relatively shorter APS spallation time.
  • the surface 2 of the turbo machine component 1 which is facing the hot gas path or hot fluid path has the second bond coat 6 coated over the first bond coat 5 to provide a better protection to the interface zone 7 from the spallation effects of hot gas or fluid.
  • the method 100 comprises a step 101 of coating a first region 3 of the turbo machine component 1 with a first bond coat 5 and a step 102 of coating a second region 4 of the turbo machine component 1 with a second bond coat 6, wherein during operation of the turbo machine component 1 the first region 3 has lower thermal loading than the second region 4, and the first bond coat 5 has a lower thermal load bearing capacity than the second bond coat 6.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13187123.8A 2013-10-02 2013-10-02 Komponente einer Turbomaschine und Verfahren zum Beschichten einer Turbomaschinenkomponente Withdrawn EP2857546A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13187123.8A EP2857546A1 (de) 2013-10-02 2013-10-02 Komponente einer Turbomaschine und Verfahren zum Beschichten einer Turbomaschinenkomponente
PCT/EP2014/068700 WO2015049086A1 (en) 2013-10-02 2014-09-03 A turbo machine component and a method of coating a turbo machine component

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EP13187123.8A EP2857546A1 (de) 2013-10-02 2013-10-02 Komponente einer Turbomaschine und Verfahren zum Beschichten einer Turbomaschinenkomponente

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EP2857546A1 true EP2857546A1 (de) 2015-04-08

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WO (1) WO2015049086A1 (de)

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EP1076158A1 (de) * 1999-08-11 2001-02-14 General Electric Company Bauteil einer Gasturbine mit positionsabhängigen Schutzbeschichtungen
US20020102360A1 (en) * 2001-01-30 2002-08-01 Siemens Westinghouse Power Corporation Thermal barrier coating applied with cold spray technique
EP1426458A1 (de) * 2002-12-06 2004-06-09 ALSTOM Technology Ltd Verfahren zur örtlichen Abscheidung einer MCrAlY - Beschichtung
WO2007140805A1 (en) * 2006-06-08 2007-12-13 Siemens Aktiengesellschaft Coated turbine component and method of coating a turbine component
EP2354454A1 (de) * 2010-02-02 2011-08-10 Siemens Aktiengesellschaft Turbinenschaufel mit variabel Oxidationsbeständiger Beschichtung

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3071732A4 (de) * 2013-11-19 2017-08-09 United Technologies Corporation Artikel mit beschichtung mit veränderlicher zusammensetzung
US11261742B2 (en) 2013-11-19 2022-03-01 Raytheon Technologies Corporation Article having variable composition coating
US11834963B2 (en) 2013-11-19 2023-12-05 Rtx Corporation Article having variable composition coating

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