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Numerical Simulation of Film Cooling on Rotating Blade Tips Within a High-Pressure Turbine

[+] Author Affiliations
K. Lu, M. T. Schobeiri, J. C. Han

Texas A&M University, College Station, TX

Paper No. GT2013-94806, pp. V03BT13A032; 13 pages
doi:10.1115/GT2013-94806
From:
  • 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

abstract

This paper numerically investigates the aerodynamics and film cooling effectiveness of high pressure turbine blade tips. Two different rotor blade tip configurations have been studied: the plane tip with tip hole cooling and the squealer tip with tip hole cooling. The geometry of the blades is determined based on the blade profiles within the three-stage multi-purpose turbine research facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL), Texas A&M University. Seven perpendicular holes along the camber line are used for the tip hole cooling. The clearance between the blade tip and casing is 1.0% of the blade span. For each blade tip configuration, the coolant is ejected through the cooling holes under blowing ratios of M = 0.5, 1.0 and 1.5. In this paper, a comparison between the plane tip and the squealer tip has been presented. The detailed flow structures and film cooling effectiveness are discussed.

Copyright © 2013 by ASME

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