Master thesis and internship[BR]- Master's thesis : Study of the leading edge flow on compressor blades and the impact of incidence[BR]- Integration Internship

Abstract

This work presents Direct Numerical simulations of a low pressure compressor cascade using a High order discontinuous Galerkin method. The High Performance Computing (HPC) massively parallel cluster, NIC5, made available by the University of Liège has made it possible to allocate a lot of resources in order to carry out the simulations. Four flow conditions are considered, which correspond to two solidities at two incidences. The flow velocity is at a Mach number of 0.45 for a corresponding Reynolds number of approximately 370 000. It is intended to understand the sudden rise of losses observed experimentally at a low solidity and a high incidence. In general, the flow field is characterized by an extremely thick boundary layer on the suction side and a laminar flow on the pressure side. For the high incidence flow, the boundary layer reaches a thickness of 10% of the chord. All the flow conditions are subjected to Laminar separation bubble and turbulent flow reattachment near the leading edge. At high incidence and low solidity, the laminar separation bubble is very thick and short, the resulting boundary layer ends to separate at 60% of the chord. Because the calculations were able to capture the complex physics of the flow. It was also able to predict the total pressure losses and flow angles, which showed a clear agreement with the experimental results.