VERIFICATION OF COMPUTATIONAL 3D MODELS OF SECONDARY FLOWS FORMATION THROUGH GAS TURBINE AIRFOIL PASSAGES BASED ON T106 PROFILE TEST
Verification was performed for computational 3D models of secondary flows formation through gas turbine airfoil passages using ANSYS CFX based on experimental data obtained by flowing high-loaded T106 cascades tested in University of Federal Armed Forces (Munich) on a test rig designed for flat turbine cascades. Analysis was performed to study the effect of computational grid parameters (Y<sub>+</sub>, mesh size) and turbulent models on turbulence modeling accuracy as well as to estimate total pressure losses and cascade exit gas angles. For steady-state RANS modeling, good agreement was observed between computational modeling data and experiment results in terms of profile nature and estimation of flow swirl angle at the cascades exit. However, total pressure net losses through the cascades were found overestimated. Recommendations were presented for identification of mesh and turbulent model parameters used in secondary flow analysis and estimation of total pressure losses through gas turbine engine cascades.