Optimization of 6.2:1 Pressure Ratio Centrifugal Compressor Impeller by 3D Inverse Design

In this work, the redesign of a centrifugal transonic compressor impeller with splitter blades by means of the three-dimensional inverse design code TURBOdesign-1 is presented

The Redesign of a Centrifugal Transonic Compressor Impeller with Splitter Blades

The basic design methodology for impellers with splitter blades is outlined and is applied in a systematic way to improve the aero/mechanical performance of a transonic 6.2:1 pressure ratio centrifugal compressor impeller

Transonic centrifugal compressors with pressure ratios higher than 5:1 are commonly used in marine diesel turbocharger applications as well as in helicopter engines and other gas turbine applications. These compressors, which tend to operate at relatively high tip speeds of 500-600 m/s, need to provide high efficiency over a broad range of operation as well as being reliable structurally.

In this paper you will:

  • Learn about the design methodology for impellers with splitter blades and why a 3D Inverse Design method is required to achieve further improvements
  • Understand the design process and objectives for this impeller redesign, which include improving efficiency at multiple speed conditions
  • Discover the final results from the optimization, including how to achieve a good compromise between suppressing secondary flows and decreasing shock losses

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