Profiling of the Turbo Compressor Inlet Nozzle of an Aircraft Engine

Using the STAR-CD software, the authors perform computational simulation of three-dimensional air flow for several configurations of the radial compressor flow channel that is used for surcharging aircraft diesel engines. The Navier — Stokes equations for viscous gas are used to describe the flow. The k–ε turbulence model is applied to account for the turbulent mixing processes. Based on the modeling results, the nozzle that provides efficient swirling with the most uniform flow at the working wheel inlet and minimal full pressure losses is chosen.

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