Towards the Large-Eddy Simulation of a full engine: Integration of a 360 azimuthal degrees fan, compressor and combustion chamber. Part I: Methodology and initialisation

Optimising the design of aviation propulsion systems using computational fluid dynamics is essential to increase their efficiency and reduce pollutant as well noise emissions. Nowadays, within this optimisation phase, it possible perform meaningful unsteady computations various components a gas-turbine engine. However, these simulations are often carried out independently each other only share averaged quantities at interfaces minimising impact interactions between components. In contrast current state-of-the-art, work presents 360 azimuthal degrees large-eddy simulation with over 2100 million cells DGEN-380 demonstrator engine enclosing fully integrated fan, compressor annular combustion chamber take-off conditions first step towards high-fidelity full order carry such challenging cost, initial solution interpolated from stand-alone sectoral component. terms approach, mesh generated in several steps solve potential machine dependent memory limitations. It then observed that computation converges an operating point less than 0.5% difference zero-dimensional values compared yielding overall performance 1% designed thermodynamic cycle. With presented methodology, convergence azimuthally decorrelated results achieved for after 6 fan revolutions.