TY - GEN
T1 - Optimum aerodynamic design of centrifugal compressor impeller using an inverse method based on meridional viscous flow analysis
AU - Oka, Nobuhito
AU - Furukawa, Masato
AU - Yamada, Kazutoyo
AU - Itou, Sasuga
AU - Ibaraki, Seiichi
AU - Iwakiri, Kenichiro
AU - Hayashi, Yoshihiro
N1 - Funding Information:
The present research was partially supported by the Japan Society for the Promotion of Science (JSPS), Grant-in-Aid for JSPS Fellows, KAKENHI 15J00212, 2015.
Publisher Copyright:
Copyright © 2017 ASME.
PY - 2017
Y1 - 2017
N2 - An optimum aerodynamic design method for centrifugal compressor impeller has been developed. The present optimum design method is using a genetic algorithm (GA) and a two-dimensional inverse blade design method based on a meridional viscous flow analysis. In the meridional viscous flow analysis, an axisymmetric viscous flow is numerically analyzed on a two-dimensional meridional grid to determine the flow distribution around the impeller. Full and splitter blade effects to the flow field are successfully evaluated in the meridional viscous flow analysis by a blade force modeling. In the inverse blade design procedure, blade loading distribution is given as the design variable. In the optimization procedure, the total pressure rise and adiabatic efficiency obtained from the meridional viscous flow analysis are employed as objective functions. Aerodynamic performance and three-dimensional flow fields in the Pareto-optimum design and conventional design cases have been investigated by three-dimensional Reynolds averaged Navier-Stokes (3D-RANS) and experimental analyses. The analyses results show performance improvements and suppressions of flow separations on the suction surfaces in the optimum design cases. Therefore, the present aerodynamic optimization using the inverse method based on the meridional viscous flow analysis is successfully achieved.
AB - An optimum aerodynamic design method for centrifugal compressor impeller has been developed. The present optimum design method is using a genetic algorithm (GA) and a two-dimensional inverse blade design method based on a meridional viscous flow analysis. In the meridional viscous flow analysis, an axisymmetric viscous flow is numerically analyzed on a two-dimensional meridional grid to determine the flow distribution around the impeller. Full and splitter blade effects to the flow field are successfully evaluated in the meridional viscous flow analysis by a blade force modeling. In the inverse blade design procedure, blade loading distribution is given as the design variable. In the optimization procedure, the total pressure rise and adiabatic efficiency obtained from the meridional viscous flow analysis are employed as objective functions. Aerodynamic performance and three-dimensional flow fields in the Pareto-optimum design and conventional design cases have been investigated by three-dimensional Reynolds averaged Navier-Stokes (3D-RANS) and experimental analyses. The analyses results show performance improvements and suppressions of flow separations on the suction surfaces in the optimum design cases. Therefore, the present aerodynamic optimization using the inverse method based on the meridional viscous flow analysis is successfully achieved.
UR - http://www.scopus.com/inward/record.url?scp=85028984244&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85028984244&partnerID=8YFLogxK
U2 - 10.1115/GT2017-63539
DO - 10.1115/GT2017-63539
M3 - Conference contribution
AN - SCOPUS:85028984244
T3 - Proceedings of the ASME Turbo Expo
BT - Turbomachinery
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
Y2 - 26 June 2017 through 30 June 2017
ER -