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Influence of High Rotational Speeds on the Heat Transfer and Discharge Coefficients in Labyrinth Seals PUBLIC ACCESS

[+] Author Affiliations
W. Waschka, S. Wittig, S. Kim

Universität Karlsruhe (T.H.), Karlsruhe, West-Germany

Paper No. 90-GT-330, pp. V004T09A037; 9 pages
doi:10.1115/90-GT-330
From:
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7907-8
  • Copyright © 1990 by ASME

abstract

Heat transfer and leakage loss measurements were obtained for compressible flows in typical straight-through labyrinth seals with high rotational speeds. The experiments are an extension of our earlier measurements in a stationary test facility. In order to ensure direct comparisons to the original experiments, the principal dimensions of the test facility and gas dynamic parameters of the hot gas were kept similar. The new study encompasses a wide range of Taylor numbers, Reynolds numbers and clearances between the rotating annular fins and the stationary shroud. Heat transfer coefficients are determined for the stator as well as for the rotor. Temperature measurements along the cooled rotor were performed utilizing a high accuracy telemetric system. Continuous clearance control was achieved by employing specially designed gauges. Detailed pressure and temperatur measurements in the axial as well as in the circumferential direction were performed. Heat transfer coefficients and loss parameters are presented and compared with those obtained under steady state conditions.

Copyright © 1990 by ASME
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