Open Science Research Excellence
@article{(International Science Index):,
  title    = {Aerodynamic Designing of Supersonic Centrifugal Compressor Stages},
  author    = {Y. Galerkin and  A. Rekstin and  K. Soldatova},
  country   = {Russian Federation},
  institution={Sankt-Petersburg State Polytechnical University},
  abstract  = {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.
    journal   = {International Journal of Mechanical, Aerospace, Industrial, Mechatronic and Manufacturing Engineering},  volume    = {9},
  number    = {1},
  year      = {2015},
  pages     = {123 - 127},
  ee        = {},
  url       = {},
  bibsource = {},
  issn      = {eISSN:1307-6892},
  publisher = {World Academy of Science, Engineering and Technology},
  index     = {International Science Index 97, 2015},