Turbofan Aeroacoustics using Wall Modeled Large Eddy Simulations скачать в хорошем качестве

Turbofan Aeroacoustics using Wall Modeled Large Eddy Simulations

The ever increasing bypass ratios on turbofans primarily motivated by fuel efficiency has led to larger fan diameters and shortened engine nacelles. Consequently, jet noise is no longer seen as the exclusive source of engine noise, with fan noise being a dominant factor at take-off and approach conditions. The fluid mechanics governing fan noise in turbofans is highly complex, with rotor-stator interactions within the duct playing a major role in overall radiated sound pressure levels. The Source Diagnostic Test (SDT) experiments conducted in the early 2000s at NASA Glenn research center attempted to shed some light on this important topic. This animation shows WMLES results for the 22-inch SDT fan rig in “approach conditions”. This simulation using 1.65 billion cells can be completed within 24-48 hours using a single server of 8x Nvidia L40S GPUs to obtain broadband acoustic predictions, as well as rotor wake turbulence characteristics. Good agreement between ScaLES and the NASA Glenn experiments (hot-wire and microphone measurements) highlight the potential of ScaLES for usage in an industrial environment given the quick solution time on very modest computational resources.