Combined Experimental and Numerical Simulations of Thermal Barrier Coated Turbine Blades Erosion

• Published in: NASA Center for AeroSpace Information (CASI). Reports
• Main Authors: Hamed, Awate, Tabakoff, Widen, Swar, Rohan, Shin, Dongyun, Woggon, Nthanial, Miller, Robert
• Format: Report
• Language: English
• Published: Hampton NASA/Langley Research Center 01.04.2013
• Subjects: Aluminum oxide; Combustion chambers; Commercial spacecraft; Compressibility; Computational fluid dynamics; Computer simulation; Equations of motion; Erosion; Impact velocity; Impingement; Ingestion; Interaction models; Mathematical models; Particle trajectories; Reynolds averaged Navier-Stokes method; Rotary wing aircraft; Simulation; Stator blades; Thermal barriers; Three dimensional models; Turbine blades; Turbines

A combined experimental and computational study was conducted to investigate the erosion of thermal barrier coated (TBC) blade surfaces by alumina particles ingestion in a single stage turbine. In the experimental investigation, tests of particle surface interactions were performed in specially designed tunnels to determine the erosion rates and particle restitution characteristics under different impact conditions. The experimental results show that the erosion rates increase with increased impingement angle, impact velocity and temperature. In the computational simulations, an Euler-Lagrangian two stage approach is used in obtaining numerical solutions to the three-dimensional compressible Reynolds Averaged Navier-Stokes equations and the particles equations of motion in each blade passage reference frame. User defined functions (UDF) were developed to represent experimentally-based correlations for particle surface interaction models which were employed in the three-dimensional particle trajectory simulations to determine the particle rebound characteristics after each surface impact. The experimentally based erosion UDF model was used to predict the TBC erosion rates on the turbine blade surfaces based on the computed statistical data of the particles impact locations, velocities and angles relative to the blade surface. Computational results are presented for the predicted TBC blade erosion in a single stage commercial APU turbine, for a NASA designed automotive turbine, and for the NASA turbine scaled for modern rotorcraft operating conditions. The erosion patterns in the turbines are discussed for uniform particle ingestion and for particle ingestion concentrated in the inner and outer 5 percent of the stator blade span representing the flow cooling the combustor liner.