EP4036272A1 - Powder, ceramic wear-protective coating for a seal, blade and method - Google Patents

Powder, ceramic wear-protective coating for a seal, blade and method Download PDF

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Publication number
EP4036272A1
EP4036272A1 EP20207058.7A EP20207058A EP4036272A1 EP 4036272 A1 EP4036272 A1 EP 4036272A1 EP 20207058 A EP20207058 A EP 20207058A EP 4036272 A1 EP4036272 A1 EP 4036272A1
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EP
European Patent Office
Prior art keywords
coating
tip
blade
zro
powder
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Withdrawn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
EP20207058.7A
Other languages
German (de)
French (fr)
Inventor
Arturo Flores Renteria
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 Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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 Energy Global GmbH and Co KG filed Critical Siemens Energy Global GmbH and Co KG
Priority to EP20207058.7A priority Critical patent/EP4036272A1/en
Publication of EP4036272A1 publication Critical patent/EP4036272A1/en
Withdrawn legal-status Critical Current

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    • 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
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
    • 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
    • C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
    • C23C26/02—Coating not provided for in groups C23C2/00 - C23C24/00 applying molten material to the 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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer 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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide 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
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C4/129—Flame 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
    • C23C4/12—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 invention relates to a ceramic coating which is used against corrosion especially of the tip seal of a turbine blade.
  • the first stages blades of a gas turbine are exposed to an extreme high temperature and a continuous degradation of their tip seal, which rub against stator components like ring segments or platforms of turbine vanes during rotation. These stationary components are normally coated with Thermal Barrier Coatings (TBC's).
  • TBC's Thermal Barrier Coatings
  • the degradation of the turbine-blade tip-seal occurs due to its poor mechanical properties against those of the TBC ceramic coating at high-temperatures. This induces an increase of the gap between the rotor with a blade tip seal and stator components, e.g. a ring segment or vane platform, and by this diminishing the efficiency of the gas turbine.
  • the figure shows a schematic view of the invention.
  • the figure shows a turbine blade 1 with a tip coating 13 on his tip 22.
  • a substrate 4 of the blade 1 is metallic and comprises especially a nickel or cobalt based superalloy.
  • the airfoil (where the reference 4 is also showing to) of the blade 1 is coated with a metallic bond coat 7, which is especially NiCoCrAl based e.g. NiCoCrAlY, NiCoCrAlYTa, NiCoCrAlYRe,... and a ceramic coating 10 (TBC), especially an Yttria stabilized Zirconia and preferably not containing Alumina Al 2 O 3 inside the coatings 7, 10; despite the Alumina which is formed during use (or after coating the TBC) by the NiCoCrAl base alloy as oxidation protection, mostly as an interlayer.
  • a metallic bond coat 7 is especially NiCoCrAl based e.g. NiCoCrAlY, NiCoCrAlYTa, NiCoCrAlYRe,... and a ceramic coating 10 (TBC), especially an Yttria stabilized Zirconia and preferably not containing Alumina Al 2 O 3 inside the coatings 7, 10; despite the Alumina which is
  • the proposal is to use a tip coating 13 to protect it additionally against high-temperature wear, wherein especially a NiCoCrAl base is bonded or coated on the tip 22 directly.
  • a NiCoCrAl based coating on the tip 22 below the tip coating 13 has preferably the same composition as on the airfoil of the blade 1.
  • the ceramic material of the powder, this tip coating 13 or seal system 16 is composed by a Zirconia toughened ceramic composed by:
  • Zirconia with amount of 40wt.% to 60wt.% and Alumina (Al 2 O 3 ) with a content 60wt.% to 40wt.% is used.
  • the ceramic material can be deposited using laser powder cladding or spray coating processes like High-Velocity Oxygen Fuel (HVOF), plasma spraying, especially Air Plasma Spray (APS) .
  • HVOF High-Velocity Oxygen Fuel
  • APS Air Plasma Spray
  • the thickness of the tip coating 13 of the seal 16 lies between 20 ⁇ m to 200 ⁇ m.
  • tip coating 13 of the tip 22 and airfoil coatings 7, 10 can be adapted, e.g. tip coating 13 can overlap coating 7, 10 (see Figure) of the airfoil or vice versa or there is no overlap or contact.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

With a new composition comprising Zirconia and Alumina a good tip seal (16) of a turbine blade (1) is reached.

Description

  • The invention relates to a ceramic coating which is used against corrosion especially of the tip seal of a turbine blade.
  • The first stages blades of a gas turbine are exposed to an extreme high temperature and a continuous degradation of their tip seal, which rub against stator components like ring segments or platforms of turbine vanes during rotation. These stationary components are normally coated with Thermal Barrier Coatings (TBC's). The degradation of the turbine-blade tip-seal occurs due to its poor mechanical properties against those of the TBC ceramic coating at high-temperatures. This induces an increase of the gap between the rotor with a blade tip seal and stator components, e.g. a ring segment or vane platform, and by this diminishing the efficiency of the gas turbine.
  • The use of a soft abradable ceramic coating deposited on the TBC surface of the stator components has proof to be a technology that diminishes the efficiency lost due to the gap opening. However, the tip seal of first stage turbine blades is still unprotected against wear-oxidation damage of its metallic material.
  • It is therefore aim of the invention to improve a seal in hot corrosion areas.
  • The problem is solved by a powder according to claim 1, a coating according to claim 2, a turbine blade according to claim 6, a seal system according to claim 10 and a method according to claim 11.
  • Up to now the use of an abrasive coating composed by cBN particles embedded in a metal matrix is under investigation. This coating system is expected to be thermal unstable during long-term operation of a turbine due to the high temperature at the blade tip seal. The standard concept is to use a soft abradable ceramic coating at the surface of the stator and a MCrAlY coated blade tip seal, which is not wear resistant at the given high-temperature conditions.
  • The figure shows a schematic view of the invention.
  • The figure shows a turbine blade 1 with a tip coating 13 on his tip 22.
  • A substrate 4 of the blade 1 is metallic and comprises especially a nickel or cobalt based superalloy.
  • The airfoil (where the reference 4 is also showing to) of the blade 1 is coated with a metallic bond coat 7, which is especially NiCoCrAl based e.g. NiCoCrAlY, NiCoCrAlYTa, NiCoCrAlYRe,... and a ceramic coating 10 (TBC), especially an Yttria stabilized Zirconia and preferably not containing Alumina Al2O3 inside the coatings 7, 10; despite the Alumina which is formed during use (or after coating the TBC) by the NiCoCrAl base alloy as oxidation protection, mostly as an interlayer.
  • The proposal is to use a tip coating 13 to protect it additionally against high-temperature wear, wherein especially a NiCoCrAl base is bonded or coated on the tip 22 directly.
  • A NiCoCrAl based coating on the tip 22 below the tip coating 13 has preferably the same composition as on the airfoil of the blade 1.
  • This is considered to be a part of a seal technology using abradable coatings on stator components.
  • The ceramic material of the powder, this tip coating 13 or seal system 16 is composed by a Zirconia toughened ceramic composed by:
    • 30wt.% - 70wt.% ZrO2 or
    • 30wt.% - 70wt.% Y2O3 - ZrO2,
      or a combination thereof and
    • 70wt.% - 30wt.% Al2O3,
      e.g. a mixture of stabilized and non-stabilized Zirconia can be used for the mixture in a total amount of 30wt.%-70wt.%.
  • Preferably Zirconia (ZrO2) with amount of 40wt.% to 60wt.% and Alumina (Al2O3) with a content 60wt.% to 40wt.% is used.
  • The ceramic material can be deposited using laser powder cladding or spray coating processes like High-Velocity Oxygen Fuel (HVOF), plasma spraying, especially Air Plasma Spray (APS) .
  • The thickness of the tip coating 13 of the seal 16 lies between 20µm to 200µm.
  • The interface 19 between tip coating 13 of the tip 22 and airfoil coatings 7, 10 can be adapted, e.g. tip coating 13 can overlap coating 7, 10 (see Figure) of the airfoil or vice versa or there is no overlap or contact.

Claims (12)

  1. Powder,
    comprising
    especially consisting of
    Zirconia (ZrO2)
    with amount of 30wt.% to 70wt.%,
    especially with amount of 40wt.% to 60wt.%,
    and
    Alumina (Al2O3)
    with a content of 70wt.% to 30wt.%,
    especially with amount of 60wt.% to 40wt.%.
  2. Coating,
    comprising
    especially consisting of
    a composition of
    30 wt. % to 70 wt. % Zirconia (ZrO2),
    especially with amount of 40wt.% to 60wt.%,
    and
    70 wt.% to 30 wt.% Alumina (Al2O3),
    especially with amount of 60wt.% to 40wt.%.
  3. Powder or coating according to one or both of the claims 1 or 2,
    which comprises at least stabilized Zirconia (ZrO2), especially a partially stabilized Zirconia (ZrO2),
    very especially only stabilized Zirconia (ZrO2).
  4. Powder or coating according to any of the claims 1, 2 or 3,
    wherein the Zirconia (ZrO2) is stabilized with Yttria (Y2O3),
    especially with 6, 0wt.% to 8,0wt.% Yttria (Y2O3) .
  5. Powder or coating according to any of the claims 1, 2, 3 or 4,
    wherein the Zirconia (ZrO2) is a mixture of stabilized and non-stabilized Zirconia (ZrO2).
  6. Turbine blade (1),
    having a tip coating (13) according to any of the claims 2, 3, 4 or 5 on the tip (22) of the blade (1),
    especially only on the tip (22) of the blade (1).
  7. Turbine blade according to claim 6,
    wherein the substrate (4) of the blade (1) is a nickel- or cobalt-based superalloy.
  8. Turbine blade according to one or both of the claims 6 or 7,
    wherein the turbine airfoil or other regions than the tip (22) of the blade (1) have protective coatings,
    especially a metallic bond (7),
    very especially NiCoCrAl based coating and
    a ceramic coating (10),
    which is much different from the tip coating (13) of the tip (22),
    especially comprises no Alumina (Al2O3) inside the coatings (7, 10).
  9. Turbine blade according to one or any of the claims 6, 7 or 8,
    wherein on tip (22) of the blade (1) a metallic bond (7), very especially a NiCoCrAl based coating,
    is present under the tip coating (13).
  10. Seal system (16) of a turbine,
    comprising a turbine blade (1) according to any of the claims 6, 7, 8 or 9.
  11. Method
    to produce
    a tip coating (13) according to claim 2
    or
    a turbine blade (1) according to claim 6, 7, 8 or 9
    or
    a seal system (16) according to claim 10,
    wherein a ceramic powder according to any of the claims 1 to 5
    is deposited by laser powder cladding
    or
    spray coating,
    especially HVOF
    or APS,
    on a tip (22) of the turbine blade (1).
  12. Method according to claim 11,
    wherein the tip coating (13) of the tip (22) has a coating thickness between 20µm to 200µm.
EP20207058.7A 2020-11-12 2020-11-12 Powder, ceramic wear-protective coating for a seal, blade and method Withdrawn EP4036272A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20207058.7A EP4036272A1 (en) 2020-11-12 2020-11-12 Powder, ceramic wear-protective coating for a seal, blade and method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20207058.7A EP4036272A1 (en) 2020-11-12 2020-11-12 Powder, ceramic wear-protective coating for a seal, blade and method

Publications (1)

Publication Number Publication Date
EP4036272A1 true EP4036272A1 (en) 2022-08-03

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117305751A (en) * 2023-09-21 2023-12-29 中国科学院金属研究所 A high thermal matching high temperature abradable sealing coating and its preparation method
DE102022211828A1 (en) 2022-11-09 2024-05-16 Siemens Energy Global GmbH & Co. KG Recoating of surfaces and components

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2121780A (en) * 1982-06-14 1984-01-04 Eutectic Corp Ceramic flame spray powder
US4588655A (en) * 1982-06-14 1986-05-13 Eutectic Corporation Ceramic flame spray powder
US5059095A (en) * 1989-10-30 1991-10-22 The Perkin-Elmer Corporation Turbine rotor blade tip coated with alumina-zirconia ceramic
WO2011107167A1 (en) * 2010-03-03 2011-09-09 Siemens Aktiengesellschaft Ceramic thermal barrier coating system with modified bonding layer

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2121780A (en) * 1982-06-14 1984-01-04 Eutectic Corp Ceramic flame spray powder
US4588655A (en) * 1982-06-14 1986-05-13 Eutectic Corporation Ceramic flame spray powder
US5059095A (en) * 1989-10-30 1991-10-22 The Perkin-Elmer Corporation Turbine rotor blade tip coated with alumina-zirconia ceramic
WO2011107167A1 (en) * 2010-03-03 2011-09-09 Siemens Aktiengesellschaft Ceramic thermal barrier coating system with modified bonding layer

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022211828A1 (en) 2022-11-09 2024-05-16 Siemens Energy Global GmbH & Co. KG Recoating of surfaces and components
CN117305751A (en) * 2023-09-21 2023-12-29 中国科学院金属研究所 A high thermal matching high temperature abradable sealing coating and its preparation method

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