DESIGN OF HIGH PRESSURE TRANSONIC MIXED FLOW COMPRESSOR

DESIGN OF HIGH PRESSURE TRANSONIC MIXED FLOW COMPRESSOR offers a comprehensive, research-oriented exploration of the aero-thermal design challenges involved in creating high-performance mixed-flow compressors for modern propulsion systems. As the demand for compact, efficient engines grows—especially in unmanned aerial vehicles (UAVs)—mixed-flow compressors have emerged as a promising solution due to their ability to deliver high pressure ratios within limited space. This book presents an in-depth investigation into the aerodynamic and thermal behavior governing such compressors, supported by rigorous numerical analysis.
The book begins by establishing the foundational principles of turbomachinery, with emphasis on compressible flow, transonic aerodynamics, blade loading, and shock–boundary layer interactions. It discusses the unique characteristics of mixed-flow compressors, which integrate axial and radial flow features to achieve superior performance in space-constrained propulsion applications. Key aero-thermal considerations such as loss minimization, temperature rise, and flow stability are examined through computational studies to provide deeper insight into the compressor’s performance across transonic operating conditions.
A major strength of this work is its extensive use of high-fidelity CFD simulations and parametric evaluations, which guide the complete aero-thermal design process. Blade shaping, flow path optimization, incidence control, turning angles, and diffuser performance are explored through iterative numerical refinement. The book includes detailed presentations of Mach number contours, static and total temperature fields, entropy generation, pressure ratio trends, and efficiency characteristics, offering deep insight into the thermofluid behavior of the compressor under transonic operating conditions.

The content directly aligns with UAV propulsion requirements, where high efficiency, compactness, and improved thermal management are essential. The aero-thermal design strategies described here provide valuable pathways for enhancing thrust capability, fuel economy, and overall propulsion system performance in small-scale gas turbines.

Serving as a key reference for researchers, engineers, and graduate students in turbomachinery and aerospace propulsion, this book blends theoretical depth with numerical precision and practical relevance. It offers a solid foundation for understanding and advancing the aero-thermal design of next-generation high-pressure transonic mixed-flow compressors.