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Investigation of the Flow Field Downstream of a Turbine Trailing Edge Cooled Nozzle Guide Vane PUBLIC ACCESS

[+] Author Affiliations
C. H. Sieverding, T. Arts, R. Dénos

von Karman Institute for Fluid Dynamics, Rhode-Saint-Genèse, Belgium

F. Martelli

University of Florence, Florence, Italy

Paper No. 94-GT-209, pp. V001T01A074; 13 pages
doi:10.1115/94-GT-209
From:
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7883-5
  • Copyright © 1994 by ASME

abstract

A trailing edge cooled low aspect ratio transonic turbine guide vane is investigated in the VKI Compression Tube Cascade Facility at an outlet Mach number M2,i s=1.05 and a coolant flow rate ṁc/ṁg=3%. The outlet flow field is surveyed by combined total-directional pressure probes and temperature probes. Special emphasis is put on the development of low blockage probes. Additional information is provided by oil flow visualizations and numerical flow visualizations with a three-dimensional Navier-Stokes code. The test results describe the strong differences in the axial evolution of the hub and tip endwall and secondary flows and demonstrate the self-similarity of the mid-span wake profiles. According to the total pressure and temperature profiles the wake mixing appears to be very fast in the near-wake but very slow in the far-wake region. The total pressure wake profile appears to be little affected by the coolant flow ejection.

Copyright © 1994 by ASME
This article is only available in the PDF format.

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