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Computational Assessment of Inlet Turbulence on Boundary Layer Development and Momentum/Thermal Wakes for High Pressure Turbine Nozzle and Blade

[+] Author Affiliations
James E. Kopriva

GE Aviation, Lynn, MANortheastern University, Boston, MA

Gregory M. Laskowski

GE Aviation, Lynn, MA

M. Reza H. Sheikhi

Northeastern University, Boston, MA

Paper No. IMECE2014-38620, pp. V08BT10A006; 13 pages
doi:10.1115/IMECE2014-38620
From:
  • ASME 2014 International Mechanical Engineering Congress and Exposition
  • Volume 8B: Heat Transfer and Thermal Engineering
  • Montreal, Quebec, Canada, November 14–20, 2014
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4956-9
  • Copyright © 2014 by ASME

abstract

A series of systematic computational studies have been conducted for transonic HPT nozzles and blades to evaluate the impact of free stream turbulence on boundary layer growth and downstream wake mixing. Transition modeling is first compared to measurements for an uncooled nozzle. The computational results are compared against measurements of loading, HTC, and wake predictions. The approach is then applied to a cooled trail-edge nozzle. The added complexity of cooling flow injection at the trail-edge showed an increase in deviation between the SST Transition model predictions and wake measurement. By applying a scale resolve model (WALE LES), wake mixing predictions are found within 1% of measurement. Finally, the computational approach is extended to a coupled uncooled nozzle/blade stage analysis. Given the favorable results for an uncooled nozzle using the SST transition model, preliminary assessment of boundary layer impact on HTC and the overall stage loss was made for the nozzle/blade stage design.

Copyright © 2014 by ASME

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