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Experimental Investigations on the Thermal Load and Leakage Flow of a Turbine Blade Tip Section With Different Tip Section Geometries

[+] Author Affiliations
Martin F. Urban, Nicolas Vortmeyer

Siemens AG, Muelheim, Germany

Paper No. 2000-GT-0196, pp. V003T01A004; 12 pages
doi:10.1115/2000-GT-0196
From:
  • ASME Turbo Expo 2000: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration
  • Munich, Germany, May 8–11, 2000
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7856-9
  • Copyright © 2000 by ASME

abstract

The gap flow across the tips of cooled rotor blades of combustion turbines is of crucial importance for the thermal load of the tip section and the stage efficiency. Various blade tip section designs with different cooling concepts were tested in a two dimensional steam cascade test rig with superheated steam as working fluid. The blade tip surface temperature distributions were measured with a thermography system and the gap flow was determined by 105 static wall pressure measurements at the opposite wall. The experimental program included systematic variations of decisive flow parameters like Mach and Reynolds numbers of the main and leakage flow as well as variations of the gap width in a range of 1.6% to 4.8% of the chord length. The performance of a simple flat blade tip served as a baseline for the comparison with advanced grooved tip designs developed in earlier studies. In addition attention was given to a systematic investigation of the influence of the coolant mass flow ejected out of the blade into the grooved tip section. The paper presents an overview of the experimental program and results as well as a discussion of the influence of the main flow and geometry parameters on the leakage flow characteristics and the accompanying thermal load of the tip section.

Copyright © 2000 by ASME

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