Thermomechanical Properties of CoNiCrAlY-BN-Polyester Composite Coatings Elaborated by Atmospheric Plasma Spraying

Aussavy, Delphine; Bolot, Rodolphe; Peyraut, François; Montavon, Ghislain; Selezneff, Serge

doi:10.4028/www.scientific.net/kem.606.167

Cited by 2 publications

(3 citation statements)

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“…The High-Pressure Compressor (HPC) and High-Pressure Turbine stages shown in Figure 1a operate at extremely high temperatures, requiring the use of materials such as NiCrAl-Bentonite and CoNiCrAlY-BN-Polyester coated on the inside circumference of casing over which turbine blades are continuously rotated to maintain clearance between the blade and casing. This is to upgrade the High-Pressure (HP) Turbine's current clearing seal, which consists of thermal barriers [31].…”

Section: Key Performance Design Considerations For Sealing Turbomachi...mentioning

confidence: 99%

“…To increase the use of coatings, a balance between spalling resistance, surface finish, erosion, and abradability is required. High-temperature damage, high-temperature exposure, creep failures, fatigue failures, corrosion failures, and failures are all eliminated [1,8,9] as well, making gas turbine blades far more reliable.…”

Section: Introductionmentioning

confidence: 99%

“…The coatings' resistance to erosion wear, adhesive strength, and performance under rub wear were tested. The study of D. Aussavy [31,32] identified the thermomechanical properties of coatings that are susceptible to abrasion. Prakash Jadhav's [33] research concerns the use of microstructure-based image models of coatings to study abradability using simulations.…”

Section: Introductionmentioning

confidence: 99%

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Microstructure Image-Based Finite Element Methodology to Design Abradable Coatings for Aero Engines

Azmeera,

Jadhav,

Lande

2023

Aerospace

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Upgrading abradable or wearable coatings in the high-temperature zone of aero engines is advised to increase the efficiency and high-density power in gas turbine engines for military or commercial fixed-wing and rotary-wing aircraft. The development of these coated materials is also motivated by minimization of the number of failures in the blade, as well as increasing their resistance to wear and erosion. It is suggested that abradable coatings or seals be used to accomplish this goal. The space between the rotor and the shroud is minimized thanks to an abradable seal at the blade’s tip. Coatings that can withstand abrasion are often multiphase materials sprayed through thermal spray methods, and which consist of a metal matAzmeerix, oxide particles, and void space. The maintenance of an ideal blend of qualities, such as erosion resistance and hardness, during production determines a seal’s effectiveness. The objective of this research is to develop microstructure-based modelling methodology which will mimic the coating wear process and subsequently help in designing the abradable coating composition. Microstructure modelling, meshing, and wear analysis using many tools such as Fusion360, Hyper Mesh, and LS-Dyna, have been employed to develop an abradable coating model and perform wear analysis using a simulated rub rig test. The relation between percentage composition and morphology variations of metal, oxide, and voids to the output parameters such as hardness, abradability, and other mechanical properties is explored using simulated finite analysis models of real micrographic images of abradable coatings.

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Section: Key Performance Design Considerations For Sealing Turbomachi...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Microstructure Image-Based Finite Element Methodology to Design Abradable Coatings for Aero Engines

Azmeera,

Jadhav,

Lande

2023

Aerospace

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Oxidation behaviour of a CoNiCrAlY/h-BN based abradable coating

et al. 2019

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This is an author's version published in: http://oatao.univ-toulouse.fr/23914 AR TICLE INFO ABST RACT Keywor ds: CoNfCrAIY/h-BN coatlng Abradable coatlngs Thennally grown oxfdes High temperature oxfdatfon resfstance The oxidation resistance of a therrnally sprayed CoNiCrAlY/h-BN abradable coating was studied at 750 and 900 •c. First, the high porosity of the abradable coating was carefully characterised in order to estimate the s peci fic surface area of the coating, required to evaluate the oxidati on kinetics. Then the forrned oxides were investigated by XRD, Raman spectroscopy and SEM. At 900 •c, the mass variations exhibited a deviation from parabolic behaviour due to rapidly growing oxides. Meanwhile, at 750 •c, after a transient state, the oxidation rate reaches a steady state, indicating that a protective alumina scale was maintained at this temperature.

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Thermomechanical Properties of CoNiCrAlY-BN-Polyester Composite Coatings Elaborated by Atmospheric Plasma Spraying

Cited by 2 publications

References 2 publications

Microstructure Image-Based Finite Element Methodology to Design Abradable Coatings for Aero Engines

Microstructure Image-Based Finite Element Methodology to Design Abradable Coatings for Aero Engines

Oxidation behaviour of a CoNiCrAlY/h-BN based abradable coating

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