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Influence of the gas-to-wall temperature ratio on the boundary layer transition: investigation of the wake behind a turbine nozzle guide vane
Formisano, P.; Ferreira, C.; Arts, T. (2019). Influence of the gas-to-wall temperature ratio on the boundary layer transition: investigation of the wake behind a turbine nozzle guide vane, in: ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition - Volume 2B: Turbomachinery. pp. 8. https://hdl.handle.net/10.1115/GT2019-91834
In: (2019). ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition - Volume 2B: Turbomachinery. American Society of Mechanical Engineers (ASME): USA. ISBN 978-0-7918-5856-1.
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Documenttype: Congresbijdrage
Auteurs  Top 
  • Formisano, P.
  • Cação Ferreira, T.S.
  • Arts, T.
Abstract
    Previous investigations performed at the von Karman Institute for Fluid Dynamics (VKI) have shown an influence of the gas-to-wall temperature ratio on the bypass transition development along the VKI LS89 blade suction side. In the present work, the influence of this quantity on the flow field downstream of this highly-loaded nozzle guide vane is studied through the evaluation of the aerodynamic losses. The investigation is organized in three sections with different combinations of exit Mach numbers and freestream turbulence intensity (FSTI) while T-gas/T-wall is varied between 1.1 and 1.3 for all the tests. The Isentropic Compression Tube facility (CT-2) at VKI allowed the determination of the total pressure loss across the cascade by means of a Pitot tube in the upstream region and a downstream three-hole needle probe. The latter is traversed in the pitch-wise direction by a pneumatic traversing system. Finally, the cascade aerodynamic efficiency is quantified by means of the kinetic energy loss coefficient zeta and the total pressure drop profile distortions in the wake region.
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