EP2669398A1 - Method of coating corner interface of turbine system - Google Patents

Method of coating corner interface of turbine system Download PDF

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Publication number
EP2669398A1
EP2669398A1 EP13169796.3A EP13169796A EP2669398A1 EP 2669398 A1 EP2669398 A1 EP 2669398A1 EP 13169796 A EP13169796 A EP 13169796A EP 2669398 A1 EP2669398 A1 EP 2669398A1
Authority
EP
European Patent Office
Prior art keywords
coating
corner interface
mesh assembly
corner
mesh
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Withdrawn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
EP13169796.3A
Other languages
German (de)
English (en)
French (fr)
Inventor
Glenn Curtis Taxacher
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2669398A1 publication Critical patent/EP2669398A1/en
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • C23C4/01—Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated

Definitions

  • the subject matter disclosed herein relates generally to gas turbine systems, and more particularly to a method of coating components within gas turbine systems.
  • components associated with rotating machinery such as compressors and turbines, for example, are subjected to a sustained high temperature, high load environment.
  • Many of the components are coated for thermal or oxidative protection, with the coating process being a particulate aerosol or plasma spray comprising particles.
  • the particles of the coating approach a surface of the component to be coated and the specific type of interaction of the particles with the surface depends on several factors, such as particle size, particle velocity, particle hardness, particle temperature, surface impingement angle, and the presence of sharp corners at the intersections of adjacent surfaces.
  • a method of coating a corner interface of a turbine system includes placing a mesh assembly proximate the corner interface. The method also includes depositing a coating onto and through the mesh assembly and into the corner interface, wherein the mesh assembly dampens a kinetic energy of the coating and secures the coating proximate the corner interface.
  • a method of coating a corner interface of a turbine component includes placing a mesh assembly proximate the corner interface, wherein the mesh assembly is removable. Also included is depositing a coating onto and through the mesh assembly and into the corner interface, wherein the mesh assembly dampens a kinetic energy of the coating and secures the coating proximate the corner interface. Further included is removing the mesh assembly from proximate the corner interface.
  • a method of coating a corner interface of a turbine component includes placing a mesh assembly proximate the corner interface. Also included is depositing a coating onto and through the mesh assembly and into the corner interface, wherein the mesh assembly dampens a kinetic energy of the coating and secures the coating proximate the corner interface, wherein the mesh assembly comprises a material that is consumable within the coating.
  • an airfoil, or a first surface 10 of a turbine bucket is illustrated and intersects with a second surface 12 that is substantially perpendicular to the first surface 10.
  • the intersection is generally referred to as a corner interface 14.
  • a coating 16 is deposited proximate the corner interface 14 and may be applied in the form of a spray, for example.
  • the coating 16 comprises a plurality of particles, including but not limited to plasma.
  • Embodiments of the present invention are not limited to any particular type of spray device.
  • Some non-limiting examples of thermal spray methods include direct current (DC) plasma spray, vacuum plasma spray, suspension plasma spray (SPS), wire-arc spray, combustion/flame spray or high-velocity oxygen fuel thermal spray process (HVOF).
  • a mesh assembly 18 is disposed proximate the corner interface 14 prior to depositing the coating 16.
  • the mesh assembly 18 functions as a dampening element, with respect to a kinetic energy possessed by particles of the coating 16. Dampening of the kinetic energy reduces the tendency of the particles from ricocheting or deflecting away from the corner interface 14, thereby resulting in stabilization of the particles as they are deposited and retention of the particles proximate the corner interface 14, as a result of a more uniform energy distribution.
  • the mesh assembly 18 may be formed of various materials and includes a plurality of apertures 20.
  • the density of the apertures 20 is dependent upon the particular application, and factors such as composition of the coating 16 and material of the corner interface 14 will influence how fine the mesh assembly 18 should be.
  • the mesh assembly 18 may be removable or consumable, as will be described in detail below. Whether the mesh assembly 18 is removable or consumable will influence what material is employed for the mesh assembly 18.
  • Such materials include, but are not limited to, woven or braided materials formed from ceramics such as Silicon Carbide (SiC) ceramic oxides including, but not limited to, those oxides of Aluminum, Silicon, and Boron, various carbon based materials, polymers and metallic alloys.
  • the suitable material of the mesh assembly 18 will depend upon composition of the coating 16 and material of the corner interface 14, but also upon whether the mesh assembly 18 is to be removable from the coating 16 or consumable within the coating 16.
  • the mesh assembly 18 may be attached to the corner interface 14 in a variety of ways, including bonding or tacking the edges of the mesh assembly 18 to the corner interface 14, for example.
  • the corner interface 14 is shown as an inner corner 22 arrangement, where the first surface 10 and the second surface 12 define an angle therebetween.
  • the angle between the first surface 10 and the second surface 12 is approximately 90 degrees, but it should be appreciated that numerous other angles are appropriate for use with the embodiments disclosed herein.
  • the corner interface 14 may include more than one mesh assembly 18 ( FIG. 2 ).
  • a plurality of mesh assemblies may be advantageous for a number or reasons, such as a desire to form a multi-layered coating 16, for example.
  • a first mesh 24 and a second mesh 26 are shown.
  • a first coating layer may be deposited into the corner interface 14 and disposed between the corner interface 14 and the first mesh 24.
  • a second coating layer is then deposited through the second mesh 26 and is therefore disposed between the first coating layer and the second mesh 26.
  • a first mesh 24 and a second mesh 26 have been shown as an example and it is contemplated that any number of meshes may be employed to provide an ability to produce multiple coating layers.
  • the coating layers may be of the same or a distinct composition and may include gaps between them, depending on the mesh assembly 18. Additional coating 16 features and advantages may be achieved by employing a split mesh assembly 28 ( FIG. 3 ), where a portion of the split mesh assembly 28 comprises a gap that allows the coating 16 to more freely enter the corner interface 14, but still retains the coating 16 by positioning of the split mesh assembly 28.
  • the first mesh 24 may be removable. By removable, it should be appreciated that the first mesh 24 is positioned and attached proximate the corner interface 14 ( FIG. 4 ) prior to depositing of the coating 16.
  • the coating 16 is then deposited toward and through the first mesh 24 until a first coating layer 30 has been formed ( FIG. 5 ).
  • the first mesh 24 is then removed and the second mesh 26, which is larger than the first mesh 24 in the illustrated example, is positioned and attached proximate the corner interface 14 ( FIG. 6 ) prior to depositing a second coating layer 32.
  • the second coating layer 32 is then deposited toward and through the second mesh 26 ( FIG. 7 ). Subsequently, the second mesh 26 is removed and the multi-layer coating 16 remains within the corner interface 14 ( FIG. 8 ).
  • the mesh assembly 18 may alternatively or conjunctively comprise one or more consumable meshes.
  • consumable it should be appreciated that one or more meshes are positioned and attached proximate the corner interface 14 prior to depositing of the coating 16, however, in contrast to the removable mesh, the consumable mesh is integrated with the coating 16 upon deposition of the coating onto and through the mesh assembly 18.
  • the consumable mesh is consumed by, or integrated with, the coating 16 in a variety of ways. First, this may be accomplished by employing a mesh that is formed of a material that is of a compatible material makeup with the coating composition, such as a Silicon Carbide (SiC) mesh used in conjunction with a ceramic coating.
  • SiC Silicon Carbide
  • a process such as fusion of the mesh due to heat of a fusion active at the time of coating may be employed.
  • a process such as fusion of the mesh due to heat of a fusion active at the time of coating may be employed.
  • Such an example is the use of a carbon or polymer mesh with a hot vapor deposition or plasma coating particles.
  • the corner interface 14 is shown as an outer corner 34 arrangement, where the first surface 10 and the second surface 12 define an angle therebetween.
  • the angle between the first surface 10 and the second surface 12 is approximately 270 degrees, but it should be appreciated that numerous other angles are appropriate for use with the embodiments disclosed herein.
  • This configuration is in contrast to the inner corner 22 arrangement described above and merely illustrates the applicability of the method with various interfaces of differing alignments.
  • the outer corner 34 arrangement may be comprised of a continuous configuration ( FIG. 10 ) or a split configuration ( FIG. 11 ).

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13169796.3A 2012-05-31 2013-05-29 Method of coating corner interface of turbine system Withdrawn EP2669398A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/485,237 US20130323430A1 (en) 2012-05-31 2012-05-31 Method of coating corner interface of turbine system

Publications (1)

Publication Number Publication Date
EP2669398A1 true EP2669398A1 (en) 2013-12-04

Family

ID=48520794

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13169796.3A Withdrawn EP2669398A1 (en) 2012-05-31 2013-05-29 Method of coating corner interface of turbine system

Country Status (5)

Country Link
US (1) US20130323430A1 (ru)
EP (1) EP2669398A1 (ru)
JP (1) JP2013249837A (ru)
CN (1) CN103452597B (ru)
RU (1) RU2013125142A (ru)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030134040A1 (en) * 2002-01-11 2003-07-17 General Electric Company-Crd Method for masking selected regions of a substrate
EP1580293A2 (en) * 2004-03-23 2005-09-28 Rolls-Royce PLC An article having a vibration damping coating and a method of applying a vibration damping coating to an article
EP2305853A1 (en) * 2009-09-30 2011-04-06 General Electric Company Method and composition for coating of honeycomb seals

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2117269B (en) * 1982-03-11 1985-08-29 Rolls Royce Thermal barrier coating
DE4432998C1 (de) * 1994-09-16 1996-04-04 Mtu Muenchen Gmbh Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren
JPH0941903A (ja) * 1995-07-27 1997-02-10 Toshiba Corp ガスタービン冷却動翼
JPH11311103A (ja) * 1998-04-27 1999-11-09 Toshiba Corp 高温部品、ガスタービン用高温部品およびこれらの製造方法
US6566635B1 (en) * 2002-03-08 2003-05-20 The Boeing Company Smart susceptor having a geometrically complex molding surface
US7028744B2 (en) * 2004-03-17 2006-04-18 National Research Council Of Canada Surface modification of castings
EP1808507A1 (de) * 2006-01-16 2007-07-18 Siemens Aktiengesellschaft Bauteil mit Beschichtung und Verfahren zum Herstellen einer Beschichtung
EP1911858B1 (de) * 2006-10-02 2012-07-11 Sulzer Metco AG Verfahren zur Herstellung einer Beschichtung mit kolumnarer Struktur

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030134040A1 (en) * 2002-01-11 2003-07-17 General Electric Company-Crd Method for masking selected regions of a substrate
EP1580293A2 (en) * 2004-03-23 2005-09-28 Rolls-Royce PLC An article having a vibration damping coating and a method of applying a vibration damping coating to an article
EP2305853A1 (en) * 2009-09-30 2011-04-06 General Electric Company Method and composition for coating of honeycomb seals

Also Published As

Publication number Publication date
RU2013125142A (ru) 2014-12-10
JP2013249837A (ja) 2013-12-12
US20130323430A1 (en) 2013-12-05
CN103452597A (zh) 2013-12-18
CN103452597B (zh) 2016-05-11

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