Free Publication

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

Written by Prof. M. Zangeneh, N. Amarel, K. Daneshkhah (Advance Design Technology) and H. Krain (DLR, Köln).

What's inside?

In this work, the redesign of a centrifugal transonic compressor impeller with splitter blades by means of the three-dimensional inverse design code TURBOdesign1 is presented. It is shown that the inverse design method could be effectively used to control the position and strength of the shock waves, eliminate flow separation and hence obtain a more uniform impeller exit flow in order to improve the aerodynamic performance. In addition, some results are presented on the comparison of stress and vibration in both impellers.

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.

Optimization of Pressure Ratio Centrifugal Compressor Impeller Cover-min

In this publication, you will:

  1. Discover the design technics to achieve a more uniform exit flow for the inverse impeller.
  2. See an efficient alternative for designing high performance impeller which is much stiffer with 1st natural frequency being 29%
    higher than the corresponding value for conventional impeller.
  3. Understand the advantage of using a 3D Inverse Design method in this project (improvements in stage efficiency, pressure ratio...).