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Abradable Seal

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A Matthews – One of the best experts on this subject based on the ideXlab platform.

  • evaluation of Abradable Seal coating mechanical properties
    Wear, 2009
    Co-Authors: A Matthews
    Abstract:

    Three proprietary plasma-sprayed coatings, based on Ni–graphite, Al–Si–graphite and Al–Si–polyester, were chosen for evaluation by the use of a (low speed) scratch tester, as a means of assessing the performance of Abradable coatings. The scratch test behaviour was also correlated with the mechanical properties of the coatings (elastic modulus, microhardness and ultimate tensile strength). The results obtained were compared with those from industrial trials, to ascertain if the scratch test could be used as a relatively cheap and effective alternative to expensive engine trials. We have shown that the Progressive Abradability Hardness, abbreviated below as PAH, can be utilised as a measure of abradability in the scratch test, and can be related to the mechanical properties, in a manner consistent with engine test-bed findings. We have also found that the abradability and the PAH can change with scratch length due, we believe, to coating compression and densification ahead of the slider. In this work, the PAH has been related to coating hardness, ultimate tensile strength and elastic modulus.

  • Evaluation of Abradable Seal coating mechanical properties
    Wear, 2009
    Co-Authors: A Matthews
    Abstract:

    International audienceThree proprietary plasma-sprayed coatings, based on Ni–graphite, Al–Si–graphite and Al–Si–polyester, were chosen for evaluation by the use of a (low speed) scratch tester, as a means of assessing the performance of Abradable coatings. The scratch test behaviour was also correlated with the mechanical properties of the coatings (elastic modulus, microhardness and ultimate tensile strength). The results obtained were compared with those from industrial trials, to ascertain if the scratch test could be used as a relatively cheap and effective alternative to expensive engine trials. We have shown that the Progressive Abradability Hardness, abbreviated below as PAH, can be utilised as a measure of abradability in the scratch test, and can be related to the mechanical properties, in a manner consistent with engine test-bed findings. We have also found that the abradability and the PAH can change with scratch length due, we believe, to coating compression and densification ahead of the slider. In this work, the PAH has been related to coating hardness, ultimate tensile strength and elastic modulus

  • investigation of Abradable Seal coating performance using scratch testing
    Surface & Coatings Technology, 2007
    Co-Authors: A Matthews
    Abstract:

    Abstract Since the real conditions at the blade tip and the casing in a gas-turbine engine present a complex (very high speed) deformation situation that is difficult and expensive to replicate, we have evaluated the use of a (low speed) standard scratch tester, as a means of assessing the performance of Abradable coatings. Three proprietary plasma-sprayed coatings, Ni-graphite, Al–Si-graphite and Al–Si-polyester, were chosen for the tests. The scratch test behaviour was correlated with the mechanical properties of each coating (elastic modulus, microhardness and UTS (ultimate tensile strength)). Our results were compared with those from industrial trials, to ascertain if the scratch test could be used as a relatively cheap and effective alternative to expensive engine trials. We have shown that the “Progressive abradability hardness” (also called “specific grooving energy”), abbreviated below as “PAH”, can be utilised as a measure of abradability in the scratch test, and can be related to the mechanical properties, in a manner consistent with engine test-bed findings. We have also found that the abradability and “PAH” can change with scratch length due to coating densification ahead of the slider, which is not easily revealed by other tests (such as the pendulum method). We therefore believe that scratch testing is a useful means of evaluating the likely in-service performance of Abradable coatings, prior to carrying out engine trials.

Djar Oquab – One of the best experts on this subject based on the ideXlab platform.

  • Thermal Barrier Systems and Multi-Layered Coatings Fabricated by Spark Plasma Sintering for the Protection of Ni-Base Superalloys
    Materials Science Forum, 2010
    Co-Authors: Daniel Monceau, Djar Oquab, Claude Estournès, Mathieu Boidot, Serge Selezneff, Nicolas Ratel-ramond
    Abstract:

    Aeronautic gas turbine blades, vanes and combustion chambers are protected against high temperature oxidation and corrosion by single or multilayered coatings. These include environmental coatings, generally based on Pt-modified Ni aluminides or MCrAlY overlays (where M = Ni and/or Co), thermal barrier coating (TBC) systems including a ceramic thermally insulating layer, and Abradable Seals. The present work shows the ability of the Spark Plasma Sintering technique to rapidly develop new coatings compositions and microstructures. This technique allows combining powders and metallic foils on a superalloy substrate in order to obtain multilayered coatings in a single short production step. Fabrication of MCrAlY overlays with local Pt and/or Al enrichments is shown, as well as fabrication of coatings made of ζ-PtAl2, ε-PtAl, α-AlNiPt2, martensitic and β-(Ni,Pt)Al or Pt-rich γ/γ’ phases, including their doping with reactive elements. The fabrication of a complete TBC system with a porous and adherent Yttria Stabilized Zirconia (YSZ) layer on a bond-coating is also demonstrated, as well as the fabrication of a CoNiCrAlY-based cermet coating for Abradable Seal application. Difficulties of fabrication are reviewed, such as Y segregation, risks of carburization, local over-heating, or difficulty to coat complex shaped parts. Solutions are given to overcome these difficulties. © (2010) Trans Tech Publications.

  • Thermal barrier systems and multi-layered coatings fabricated by spark plasma sintering for the protection of Ni-base superalloys
    Materials Science Forum, 2010
    Co-Authors: Daniel Monceau, Djar Oquab, Claude Estournès, Mathieu Boidot, Serge Selezneff, Nicolas Ratel-ramond
    Abstract:

    Aeronautic gas turbine blades, vanes and combustion chambers are protected against high temperature oxidation and corrosion by single or multilayered coatings. These include environmental coatings, generally based on Pt-modified Ni aluminides or MCrAlY overlays (where M = Ni and/or Co), thermal barrier coating (TBC) systems including a ceramic thermally insulating layer, and Abradable Seals. The present work shows the ability of the Spark Plasma Sintering technique to rapidly develop new coatings compositions and microstructures. This technique allows combining powders and metallic foils on a superalloy substrate in order to obtain multilayered coatings in a single short production step. Fabrication of MCrAlY overlays with local Pt and/or Al enrichments is shown, as well as fabrication of coatings made of -PtAl2, -PtAl, α-AlNiPt2, martensitic and (Ni,Pt)Al or Pt-rich ’ phases, including their doping with reactive elements. The fabrication of a complete TBC system with a porous and adherent Yttria Stabilized Zirconia (YSZ) layer on a bond-coating is also demonstrated, as well as the fabrication of a CoNiCrAlY-based cermet coating for Abradable Seal application. Difficulties of fabrication are reviewed, such as Y segregation, risks of carburization, local over-heating, or difficulty to coat complex shaped parts. Solutions are given to overcome these difficulties.

  • Reactivity and microstructure evolution of a CoNiCrAlY/Talc cermet prepared by Spark Plasma Sintering
    Surface and Coatings Technology, 2010
    Co-Authors: Nicolas Ratel-ramond, Daniel Monceau, Claude Estournès, Djar Oquab
    Abstract:

    A mixture of CoNiCrAlY and talc powders is considered as a new candidate composition for Abradable Seal coating applications. Dense specimen having the composition of 1:20 weight ratio of talc with respect to CoNiCrAlY was prepared using the Spark Plasma Sintering (SPS) technique. The aim of the present article is to investigate the reactivity and microstructure evolution of the β/γ-CoNiCrAlY based cermet. The resulting microstructures were analysed and their compositions determined using standard analytical techniques such as SEM, TEM and X-ray diffraction. After fabrication, the bulk of the material is shown to contain a continuous oxide layer of MgAl2O4 at the periphery of metallic particles, resulting from the reaction between aluminium, which has diffused from the bulk of CoNiCrAlY grains, with magnesium and oxygen delivered during the high temperature decomposition of the talc phase. Thermodynamic calculations results are found to be consistent with the experimental observations. The oxidation behaviour at a high temperature of this cermet was also investigated. It was shown that at its external surface a continuous double layer is formed — one external film at the surface of the sample made of MgAl2O4 and the second one more internal in between the later and the cermet made of α-Al2O3. The oxide scale is protective with low oxidation kinetics typical of alpha alumina growth (kP = 1.8 ⋅ 10 − 7mg2 ⋅ cm − 4 ⋅ s − 1 at 1050 °C in flowing dry air).

Nicolas Ratel-ramond – One of the best experts on this subject based on the ideXlab platform.

  • Thermal Barrier Systems and Multi-Layered Coatings Fabricated by Spark Plasma Sintering for the Protection of Ni-Base Superalloys
    Materials Science Forum, 2010
    Co-Authors: Daniel Monceau, Djar Oquab, Claude Estournès, Mathieu Boidot, Serge Selezneff, Nicolas Ratel-ramond
    Abstract:

    Aeronautic gas turbine blades, vanes and combustion chambers are protected against high temperature oxidation and corrosion by single or multilayered coatings. These include environmental coatings, generally based on Pt-modified Ni aluminides or MCrAlY overlays (where M = Ni and/or Co), thermal barrier coating (TBC) systems including a ceramic thermally insulating layer, and Abradable Seals. The present work shows the ability of the Spark Plasma Sintering technique to rapidly develop new coatings compositions and microstructures. This technique allows combining powders and metallic foils on a superalloy substrate in order to obtain multilayered coatings in a single short production step. Fabrication of MCrAlY overlays with local Pt and/or Al enrichments is shown, as well as fabrication of coatings made of ζ-PtAl2, ε-PtAl, α-AlNiPt2, martensitic and β-(Ni,Pt)Al or Pt-rich γ/γ’ phases, including their doping with reactive elements. The fabrication of a complete TBC system with a porous and adherent Yttria Stabilized Zirconia (YSZ) layer on a bond-coating is also demonstrated, as well as the fabrication of a CoNiCrAlY-based cermet coating for Abradable Seal application. Difficulties of fabrication are reviewed, such as Y segregation, risks of carburization, local over-heating, or difficulty to coat complex shaped parts. Solutions are given to overcome these difficulties. © (2010) Trans Tech Publications.

  • Thermal barrier systems and multi-layered coatings fabricated by spark plasma sintering for the protection of Ni-base superalloys
    Materials Science Forum, 2010
    Co-Authors: Daniel Monceau, Djar Oquab, Claude Estournès, Mathieu Boidot, Serge Selezneff, Nicolas Ratel-ramond
    Abstract:

    Aeronautic gas turbine blades, vanes and combustion chambers are protected against high temperature oxidation and corrosion by single or multilayered coatings. These include environmental coatings, generally based on Pt-modified Ni aluminides or MCrAlY overlays (where M = Ni and/or Co), thermal barrier coating (TBC) systems including a ceramic thermally insulating layer, and Abradable Seals. The present work shows the ability of the Spark Plasma Sintering technique to rapidly develop new coatings compositions and microstructures. This technique allows combining powders and metallic foils on a superalloy substrate in order to obtain multilayered coatings in a single short production step. Fabrication of MCrAlY overlays with local Pt and/or Al enrichments is shown, as well as fabrication of coatings made of -PtAl2, -PtAl, α-AlNiPt2, martensitic and (Ni,Pt)Al or Pt-rich ’ phases, including their doping with reactive elements. The fabrication of a complete TBC system with a porous and adherent Yttria Stabilized Zirconia (YSZ) layer on a bond-coating is also demonstrated, as well as the fabrication of a CoNiCrAlY-based cermet coating for Abradable Seal application. Difficulties of fabrication are reviewed, such as Y segregation, risks of carburization, local over-heating, or difficulty to coat complex shaped parts. Solutions are given to overcome these difficulties.

  • Reactivity and microstructure evolution of a CoNiCrAlY/Talc cermet prepared by Spark Plasma Sintering
    Surface and Coatings Technology, 2010
    Co-Authors: Nicolas Ratel-ramond, Daniel Monceau, Claude Estournès, Djar Oquab
    Abstract:

    A mixture of CoNiCrAlY and talc powders is considered as a new candidate composition for Abradable Seal coating applications. Dense specimen having the composition of 1:20 weight ratio of talc with respect to CoNiCrAlY was prepared using the Spark Plasma Sintering (SPS) technique. The aim of the present article is to investigate the reactivity and microstructure evolution of the β/γ-CoNiCrAlY based cermet. The resulting microstructures were analysed and their compositions determined using standard analytical techniques such as SEM, TEM and X-ray diffraction. After fabrication, the bulk of the material is shown to contain a continuous oxide layer of MgAl2O4 at the periphery of metallic particles, resulting from the reaction between aluminium, which has diffused from the bulk of CoNiCrAlY grains, with magnesium and oxygen delivered during the high temperature decomposition of the talc phase. Thermodynamic calculations results are found to be consistent with the experimental observations. The oxidation behaviour at a high temperature of this cermet was also investigated. It was shown that at its external surface a continuous double layer is formed — one external film at the surface of the sample made of MgAl2O4 and the second one more internal in between the later and the cermet made of α-Al2O3. The oxide scale is protective with low oxidation kinetics typical of alpha alumina growth (kP = 1.8 ⋅ 10 − 7mg2 ⋅ cm − 4 ⋅ s − 1 at 1050 °C in flowing dry air).