Numerical Simulations and Design Optimization of Compressor Cascade Flow Using One Equation and Wray-Agarwal Turbulence Model

The unsteady simulations are conducted, and the computed results with WA model are compared with the experimental data in conjunction with the simulation results obtained using traditional models. It is shown that on the mid-span sections of the cascade airfoils the distributions of near-wall static pressure coefficients from each turbulence model agree well with the experimental data. On the lower spanwise sections, the discrepancy between the numerical simulations and experimental data generally increases. Among the three turbulence models, the WA turbulence model shows better agreement with the experimental data in predicting the spanwise total pressure losses downstream of the cascade blade. The WA model is then embedded into the adjoint optimisation loop to test its capability in minimising the flow losses in the compressor cascade passage. The optimisation results show that the total pressure loss coefficient of the optimised compressor cascade is reduced by 18.1% compared to the baseline design.