Loss Analysis of a Transonic Rotor with a Differential Approach to Entropy Generation

The loss mechanism of transonic axial compressors is a long-standing problem that involves almost all types entropy generation in fluid flows, such as skin friction, shock waves, shear corner separation, and tip vortices. Primarily, sources need to be identified quantitative comparisons their contributions made. For determination, we propose herein differential approach generation, called the “differential approach”. Two case studies are analyzed determine applicability this approach: (1) laminar turbulent incompressible flows straight circular ducts (2) compressible convergent-and-divergent nozzles with waves. results lead following conclusions: (a) Qualitatively, works well, quantified measure reliable if it calculated quality meshes suitable turbulence model. This means can good tool for predesign optimization. (b) When shocks occur within flow fields, shock-induced boundary-layer separation generate more than alone. Subsequently, applied complex NASA Rotor 67, which well-known bench-test rotor. show not only determines local losses associates source structures but also qualitatively compares identifies largest contributors. These provide theoretical foundation optimizing rotor design enhancing stability.