The Axial Flow Compressor Transonic Three-dimensional Flow Field Numerical Simulation

The blade of the transonic axial flow compressor is usually twistable. From blade root to tip, the blade profile camber and the setting angle are different. The internal flow field of the transonic axial flow compressor is very complex for its extremely complex geometry. Because of these characteristics, the production of the boundary condition, the grid and the numerical simulation are very difficult to achieve. Therefore, the constitution of an accurate numerical analysis system for the transonic axial compressor becomes more and more prevalent.Based on the theoretical analysis of three-dimensional flows in transonic axial flow compressor, the author establishes its analysis model, and uses Euler equations as the control equations to compute the flow field by programming the FORTRAN codes. The proper three dimensional grids are generated by algebraic method. Euler equations are solved by using Multistage Runge-Kutta explicit scheme, and then the numerical results are obtained through time-marching method. The suitable initial condition and boundary condition are supposed to meet stable computation in the paper. Considering the existing of the shock, artificial viscosity is added to the equations.NASA ROTOR 37 and NASA ROTOR 67 are applied in the program to prove the validation and the reliability of the method. The numerical results are partly compared with the experimental data and those of the commercial software. All the results are consistent with the actual working principle of the transonic axial compressor. This shows that the method established in this paper is practicable. The program has a simple chart and converges fast. In addition, the program offers a basic method to compute the internal three-dimensional flow field of the high speed axial compressor.