Separated Flow in a Straight Compressor Cascade

  • J. Citavý
  • M. Dušek
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

Summary

Experimental results are presented concerning separated incompressible flow through two linear compressor cascades at off-design conditions. The first cascade denoted as RK3 has already been tested at high positive and low negative incidence angles. The second cascade having NACA 65–1810 profile was measured at high positive incidence angle. The experiments covered loss coefficient and deviation angle within the blade row and at various distances behind the trailing edge, as well as the blade surface pressure distribution and flow visualisation. The experimental results have been compared with the viscous flow calculation and a reasonable qualitative agreement has been obtained. More comparison is needed before any reliable prediction could be made.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

Literature

  1. 1.
    Howel, A.R.:The present basis of axial flow compressor design Part I: Cascade theory and performance. Brit. Aeronaut. Research Council Repts and Mem. 2095, 1942Google Scholar
  2. 2.
    Citavý, J.: Performance prediction of straight compressor cascade having an arbitrary profile shape. ASME J. Turbom., 109, 1987, pp. 114–122CrossRefGoogle Scholar
  3. 3.
    Chauvin, J., Gerolymos, G.A., Jazigi, N., Charlier, M.H.: Performance prediction of subsonic separated cascades. ASME paper, No GT-65 Brussels 1990Google Scholar
  4. 4.
    Hah, C., 1986 A numerical modelling of endwall and tips- clearence flow of an isolated compressor rotor. ASME Journal of Engineering for Gas Turbines and Power, Vol. 108, pp 15–21CrossRefGoogle Scholar
  5. 5.
    Citavý, J.: Two-dimensional compressor cascades with optimum velocity distribution over the blade. ASME Journal of Engineering for Power, 1975, pp 101–110Google Scholar
  6. 6.
    Citavý, J.: Boundary layer on straight compressor casca des 1st Conference on Mechanics, Proceedings torn 8 volume, Praha 1987Google Scholar
  7. 7.
    Citavý, J., Dušek, M.: Visualisation of boundary layers aerofoils. Conference on Visualisation Praha 1989Google Scholar
  8. 8.
    Zuber, I.:Numerical solution of the turbulent flow of an incompressible fluid in curved planar and axially symmetrical channels. Int. J. Heat Fluid Flow, Vol. 3, No 2, June 1982Google Scholar
  9. 9.
    Solanikova, J., Zuber, I.: Numerical solution of a viscous incompressible flow past a cascade of profiles. Research report SVÚSS 77–04003Google Scholar
  10. 10.
    Polašek, J.: Calculation of coefficients of induced velocities in cascades with slightly bended profiles. Research report SVÚTT 58–01027.Google Scholar

Copyright information

© Springer-Verlag, Berlin Heidelberg 1991

Authors and Affiliations

  • J. Citavý
    • 1
  • M. Dušek
    • 1
  1. 1.National Research Institute for Machine design (SVÚSS)Prague 9 - BĕchoviceCzechoslovakia

Personalised recommendations