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A fast and accurate numerical method for solving the two dimensional Reynolds aveaged Navier Stokes is applied to calculate the internal fluid of turbines and compressors. The code is based onan explicit, time-marching, finite volume technique. In order to accelerate convergence, local time stepping, multigrid method is employed. Four stage Runge-Kutta method is implemented to extend the stability domain. Test cases of Hobson’s impulse cascade, NASA Rotor 37 and Sanz’s supercritical compressor cascade are presented. Results of Mach number distribution on blade surfaces and Mach number contour plots indicate good agreement with experimental data. Compared with full three 3D Navier-Stokes (N-S) codes, the two dimensional code only takes a short time to obtain predicted results. This code can be used widely in practical engineering design.
A fast and accurate numerical method for solving the two dimensional Reynolds aveaged Navier Stokes is applied to calculate the internal fluid of turbines and compressors. The code is based onan explicit, time-marching, finite volume technique. In order to accelerate convergence, local time Four-stage Runge-Kutta method is implemented to extend the stability domain. Test cases of Hobson’s impulse cascade, NASA Rotor 37 and Sanz’s supercritical compressor cascade are presented. Results of Mach number distribution on blade surfaces and Mach number Compared with full three 3D Navier-Stokes (NS) codes, the two dimensional code only takes a short time to obtain the predicted results. This code can be used widely in practical engineering design.