Optimizing Pressure Rise in Transonic Axial Compressor Stage Using Tandem Rotors

Axial flow compressors play a crucial role in various engineering applications, particularly in aerospace and industrial power generation. Their efficiency and performance directly impact system reliability, making continuous advancements in compressor blade design essential. This study focuses on the comparative aerodynamic analysis of single and tandem rotor blade configurations in a transonic axial flow compressor using Computational Fluid Dynamics (CFD) simulations. The primary objective is to assess how tandem rotor configurations influence pressure rise, flow uniformity, and overall compressor efficiency compared to traditional single rotor designs. The tandem rotor arrangement, which incorporates two sequential blades within a single stage, is hypothesized to reduce flow separation, minimize aerodynamic losses, and improve pressure recovery. Through high-fidelity 2D CFD simulations, comparison of total pressure ratios of single and tandem rotor configurations were done. The results indicate that tandem rotor configurations exhibit a notable improvement in total pressure rise and efficiency, demonstrating their potential in enhancing compressor performance. Additionally, the study explores optimal inter-blade spacing and stagger angles to further refine tandem blade effectiveness. While challenges in design complexity and manufacturing exist, ongoing advancements in CFD modelling and materials science are paving the way for practical implementation of tandem rotor technology. This research contributes to the development of more energy-efficient and high-performance axial compressors, addressing the growing need for improved aerodynamic efficiency and operational stability in modern turbo machinery applications.