Unsteady Flow Analysis of the Full Annulus and Complete Low-Pressure ENOVAL Transonic Compressor

Abstract For the next generation of aircraft engines, the ultra-high bypass ratio configuration is one of the challenges to be met. In this architecture, the fan and low-pressure compressor are separated by a gearbox, which implies the appearance of high-speed compressor. Compressibility effects are therefore amplified and contribute to rotor-stator interactions. Thus, the aim of this study is to carry out unsteady simulations of the complete and full-annulus low-pressure ENOVAL compressor and to perform the analysis of the unsteady performances and flow patterns. The use of probability mass function exhibits particular fluctuations of stagnation pressure downstream each stator, except the last one, and on wall static pressure. The analysis of shock pattern shows that the origin of this behavior is due to propagation of rotor shock wave in stator domains, and to reflected wave generated at trailing edge.