CONSTRUCTION OF A COMPRESSOR STAGE BLADE ROW ACCORDING TO THE GAS-DYNAMIC CALCULATION

Authors

  • M. Bogdanov National aviation university
  • P. Grekov National aviation university
  • K. Kapitanchyk National aviation university
  • I. Lastivka National aviation university

DOI:

https://doi.org/10.18372/2310-5461.13.5009

Keywords:

axial-flow compressor, blade row, profile thickness, coordinate of profile row. stave designing

Abstract

In research presented methodology of blade nm construction according to the gas-dynamic calculation. This methodology permit at first approximation obtain coordinate of section face and tray of blade row subject to angles of setting, profile curature, profile thickness ration by height o blade row.

References

Холщевников К. В. Теория и расчет авиационных лопаточных машин/ К. В. Холщевников. — М. : Машиностроение, 1970. — 610 с.

Терещенко Ю. М. Газодинамический расчет ступени компрессора и турбины газотурбинного двигателя/ Ю. М. Терещенко. — К. : КВВАИУ, 1974. — 78 с.

Юрин А. В. Выбор основных параметров и расчет осевого многоступенчатого компрессо-ра/ А. В. Юрин. — Куйбышев: КАИ, 1970. — 103 с.

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Published

2011-11-14

How to Cite

Bogdanov, M., Grekov, P., Kapitanchyk, K., & Lastivka, I. (2011). CONSTRUCTION OF A COMPRESSOR STAGE BLADE ROW ACCORDING TO THE GAS-DYNAMIC CALCULATION. Science-Based Technologies, 13(1), 5–8. https://doi.org/10.18372/2310-5461.13.5009

Issue

Vol. 13 No. 1 (2012)

Section

Avionics and Engineering

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