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Numerical Investigations of Wake and Shock Wave Effects on Film Cooling Performance in a Transonic Turbine Stage: Part 2 — Unsteadiness Effect in a 2D Rotating Passage

[+] Author Affiliations
Huazhao Xu, Jianhua Wang

University of Science and Technology of China, Hefei, China

Ting Wang

University of New Orleans, New Orleans, LA

Paper No. GT2013-94545, pp. V03BT13A019; 10 pages
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 3B: Heat Transfer
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5515-7
  • Copyright © 2013 by ASME


Using the validated CFD model and realizable k-ε turbulence model from Part 1, the unsteadiness effects of shock waves and wake flow on the pressure coefficient and film cooling performance in a 2-D, rotating passage is studied in Part 2. Both time-dependent and time-averaged cooling effectiveness distributions on the rotor under the influence of shock waves and unsteady wake flows are presented with blowing ratios of 0.5, 1.0, and 1.5. The results show that (a) the unsteady wake passing caused by the blade rotation significantly influences the time-dependent pressure coefficients, especially in the forward region downstream of the stagnation point on both the suction and pressure sides on the rotor. This effect can be evidenced by the “wrapping behavior” of a strong vorticity field wrapping around the blade leading edge after the wake hit the blade (b) On the suction side, over the crown area of the rotor, the wake-induced pressure fluctuations are augmented by the weak shock wave emanating from the stator’s trailing edge, appearing as a primary peak followed by a secondary peak. The weak oblique shock wave can be evidenced by the dense Mach contour curves. The effect of the wake (rotational) is distinguished from that of the shock (inviscid and non-rotational) by comparing the pressure gradient field with the vorticity field. (c) Similar effects of passing wakes and shock waves on the surface pressure on a rotor are observed on the film cooling effectiveness, except that these effects are of the same magnitude. (d) The effect of the blowing ratio on the static pressure distribution at the rotor wall is not significant, whereas its effect on the film cooling effectiveness is more pronounced.

Copyright © 2013 by ASME



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