Universal modeling method well proven for industrial
compressors was applied for design of the high flow rate supersonic
stage. Results were checked by ANSYS CFX and NUMECA Fine
Turbo calculations. The impeller appeared to be very effective at
transonic flow velocities. Stator elements efficiency is acceptable at
design Mach numbers too. Their loss coefficient versus inlet flow
angle performances correlates well with Universal modeling
prediction. The impeller demonstrates ability of satisfactory operation
at design flow rate. Supersonic flow behavior in the impeller inducer
at the shroud blade to blade surface Φ des deserves additional study.
 Galerkin, Y.B., Soldatova, K.V., Drozdov, A.A. Turbo compressor
efficiency application and calculation. (text) // Compressors &
Pneumatics. – 2011. – No. 8. – Page 2-11. (in Russian).
 Galerkin Y.B., Drozdov A.A., Soldatova K.V. (SPbSTU). Improvement
of method to calculate industrial centrifugal compressors performance.
(text) // Compressors & Pneumatics.. – № 8. – 2013. – С. 24-32. (in
 Soldatova K.V. Universal modeling method application for development
centrifugal compressor model stages. Conference «Compressors and
their Systems». – London. – 2013. - P. 477-487. (in English).
 Transactions of the 2nd Open Conference of Users of NUMECA in
Russia. – 2013.
 Galerkin, Y.B Turbocompressors. - Мoscow. - 2010. – С. 596. (in