Severe erosion and corrosion damages when hard particles are ingested for example in a gas turbine engine
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The objective of this work was to determine erosion resistance of advanced thermal barrier coating systems under simulated engine erosion and thermal gradient environments, thus validating a new thermal barrier coating turbine blade technology for future rotorcraft applications. A high velocity burner rig based erosion test approach was established and a new series of rare earth oxide- and TiO2/Ta2O5- alloyed, ZrO2-based low conductivity thermal barrier coatings were designed and processed. The low conductivity thermal barrier coating systems demonstrated significant improvements in the erosion resistance. A comprehensive model based on accumulated strain damage low cycle fatigue is formulated for blade erosion life prediction. The work is currently aiming at the simulated engine erosion testing of advanced thermal barrier coated turbine blades to establish and validate the coating life prediction models
High temperature erosion testing development
─ High velocity burner erosion rig simulating engine environments
─ Computational Fluid Dynamics (CFD) modeling
─ Experimental validation of high temperature erosion testing
• Low conductivity turbine thermal barrier coating developments
─ Low conductivity TBC design approach
─ High toughness erosion resistant turbine airfoil TBC development
─ Calcium-magnesium-alumino-silicate (CMAS) interaction testing
• Coating Performance and Life Prediction
─ High toughness turbine erosion coating modeling
─ Sintering-creep, oxidation and thermo-mechanical fatigue mechanisms
Ref:Performance Evaluation and Modeling of ErosionResistant Turbine Engine Thermal Barrier Coatings
Dr. Robert A. Miller, Dr. Dongming Zhu *, Dr. Maria Kuczmarski
Fundamental Aeronautics Program Annual Meeting, October 7-9, 2008
ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20130013140.pdf
by RA Miller - 2008