Experimental and Numerical Investigation on Finned Vortex Reducer in a Rotating Cavity with a Radial Inflow

In aero-engines, a secondary air system is used to cool the rotor discs and seal cavities between stator parts. The pressure loss caused by bleed can be effectively reduced setting finned vortex reducer. Thus, design optimized researching flow structure of each section in cavity with this study, influence different installation positions reducer on characteristics was investigated through experimental numerical simulation methods, focusing radial inflow system. results indicate that inlet outlet fins affect cavity. aerodynamic parameters (rotational Reynolds number ReΦ mass rate coefficient Cw), together radii fins, Considering swirl ratio β constrained model established, which showed good agreement experimentally measured loss. This reflects impact characteristics.