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Implicit Large Eddy Simulation of a Stalled Low Pressure Turbine Airfoil

[+] Author Affiliations
C. L. Memory, J. P. Chen, J. P. Bons

The Ohio State University, Columbus, OH

Paper No. GT2015-43792, pp. V02AT38A038; 12 pages
doi:10.1115/GT2015-43792
From:
  • ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
  • Volume 2A: Turbomachinery
  • Montreal, Quebec, Canada, June 15–19, 2015
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5663-5
  • Copyright © 2015 by ASME

abstract

Time-accurate numerical simulations were conducted on the aft-loaded L1A low pressure turbine airfoil at a Reynolds number of 22,000 (based on inlet velocity magnitude and axial chord length). This flow condition produces a non-reattaching laminar separation zone on the airfoil suction surface. The numerical code TURBO is used to simulate this flow field as an Implicit Large Eddy Simulation. Generally good agreement was found when compared to experimental time-averaged and instantaneous flow measurements. The numerical separation zone is slightly larger than that in the experiments, though integrated wake loss values improved from RANS-based simulations. Instantaneous snapshots of the numerical flow field showed the Kelvin Helmholtz instability forming in the separated shear layer and a large-scale vortex shedding pattern at the airfoil trailing edge. These features were observed in the experiments with similar sizes and vorticity levels. Power spectral density analyses revealed a global passage oscillation in the numerics that was not observed experimentally. This oscillation was most likely a primary resonant frequency of the numerical domain.

Copyright © 2015 by ASME

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