Design and numerical aerodynamic analysis of a centrifugal compressor impeller for a 100 kgf-thrust gas turbine engine
DOI:
https://doi.org/10.54939/1859-1043.j.mst.110.2026.159-168Keywords:
Small gas turbine engine; Centrifugal compressor; Impeller; CFD; Aerodynamic characteristics.Abstract
Small gas turbine engines with 100 kg thrust are increasingly used in unmanned aerial vehicles (UAVs) and small aerospace propulsion systems. In these engines, centrifugal compressors are preferred for their compact design, high compression ratio, and high isothermal efficiency. This study presents the preliminary design and computational fluid dynamics (CFD)-based aerodynamic investigation of a centrifugal compressor impeller. A complete three-dimensional geometry was developed from the target operating parameters, and Reynolds-averaged Navier-Stokes simulations with k-SST turbulence modeling were performed to analyze the internal flow field and evaluate the impeller's aerodynamic performance. The numerical results showed that the total pressure ratio and efficiency were 4.505 and 85.007% at the design point, and the near-stall margin achieved at 18.056% within the typical requirements of a gas turbine engine compressor.
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