Numerical solution of compressor cascade aerodynamic optimization problems

Information from scientific report at the meeting of Presidium of NAS of Ukraine October 8, 2014

Authors

  • S.V. Melashych Institute of Technical Mechanics of National Academy of Sciences of Ukraine and State Space Agency of Ukraine, Dnipropetrovsk

Keywords:

compressor cascade, aerodynamic optimization, inverse design, numerical simulation

Abstract

The scientific and methodological support for a comprehensive approach to the aerodynamic design and optimization of compressor cascades profiles is developed. The mentioned above scientific and methodological support can be used for the determination of the compressor blades rational geometric parameters of aircraft gas turbine engines compressor rims at the design stage, as well as for the study of the flow structure in the compressor cascades and predicting their aerodynamic characteristics in the operating range of the mode parameters. Specific scientific and methodological developments are introduced on the SE «Ivchenko-Progress» (Zaporozhye) and they are currently used in the design of compressor blade rims of modern gas turbine engines.

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Published

2015-01-26

How to Cite

Melashych, S. (2015). Numerical solution of compressor cascade aerodynamic optimization problems: Information from scientific report at the meeting of Presidium of NAS of Ukraine October 8, 2014. Visnyk of the National Academy of Sciences of Ukraine, (1), 62–66. Retrieved from https://nasu-periodicals.org.ua/index.php/visnyk/article/view/6093

Issue

No. 1 (2015): Visnyk of the National Academy of Sciences of Ukraine

Section

YOUNG SCIENTISTS