Causal Effect of Leading-Edge Sawtooth Configuration on Flow Field Characteristics and Aerodynamic Losses in the Supersonic Compressor Cascade

Abstract

This study focuses on the TM-141 supersonic compressor blade as the subject of investigation. Utilizing the Reynolds-averaged numerical simulation approach, the study examines the impact of the leading-edge sawtooth structure on the blade grid, flow field characteristics, and flow losses. Comparative analysis is conducted between numerical results and experimental data to assess the influence of the leading-edge sawtooth structure under various conditions, including fixed Mach numbers and variable static pressure ratios, fixed static pressure ratios and variable Mach numbers, and fixed Mach numbers and fixed static pressure ratios. The findings reveal that the leading-edge sawtooth structure effectively alters the distribution of total pressure loss coefficients within the blade grid channels, mitigates leading-edge spikes, and improves trailing-edge blade morphology, consequently reducing trailing-edge losses and total pressure loss compared to benchmark blade grids. These results offer insights for mitigating losses and enhancing efficiency in the transonic region of compressor blade operation, thereby providing a foundation for further investigation into the effects of leading-edge sawtooth structures on flow fields.

Keywords

• leading
• edge sawtooth transonic compressor cascade cascade characteristics aerodynamic shock wave /boundary layer interaction