Nozzle Guide Vane Shock Wave Propagation and Bifurcation in a Transonic Turbine Rotor PUBLIC ACCESS

[+] Author Affiliations
A. B. Johnson, M. L. G. Oldfield

Oxford University, Oxford, England

M. J. Rigby

Rolls Royce Plc, Derby, England

M. B. Giles

M. I. T., Boston, MA

Paper No. 90-GT-310, pp. V001T01A095; 8 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


A study of the propagation of a Nozzle Guide Vane (NGV) trailing edge shock wave through a transonic turbine rotor passage is presented. The work was based on experimental tests carried out in the Isentropic Light Piston Tunnel in Oxford University using a rotating bar NGV shock wave simulator, together with schlieren photography and wide band width surface pressure and heat transfer rate measurements.

The study identifies a previously unexplained interaction between the incoming wave and the rotor leading edge, which causes the nucleation of a Vortical Bubble. This bubble has been shown to enhance the thermal loading on the early pressure surface of the blade. A method of controlling this bubble and heat loading is also considered.

A previously unseen “Lambda” interaction between the shock wave and the rotor pressure surface is also identified.

Copyright © 1990 by ASME
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