Development and Application of the Sliding Plane Method for Turbomachinery

This study focuses on the development and application of the sliding plane method for turbomachinery. The implementation of sliding plane consists of two parts: (1) grid manipulation in pre-processor and (2) sliding mesh interpolation in solver. In pre-processor phase, mesh extrusion, donor-receptor search pairing, and geometric array updates algorithms are implemented. Based on the updated grid information in pre-processor phase, flux interpolation between pairwise sliding planes is developed for unsteady Raynolds-averaged simulation (RANS). To validate the performance of our sliding plane method, the comparative simulation with the mixing plane method on Transonic Compressor Darmstadt (TCD) at Technical University of Darmstadt (TUDa) case is conducted using both sliding boundary and hybrid boundary methods. Special concern is placed on the stall phenomena near the leading edge of the compressor under near-stall conditions. Numerical results show superior agreement with experimental data compared to the mixing plane results, affirming its effectiveness in simulating unsteady conditions.