Effects of Tip Endwall Contouring on the Three Dimensional Flow Field in an Annular Turbine Nozzle Guide Vane: Part 2 — Numerical Investigation PUBLIC ACCESS

[+] Author Affiliations
Tony Arts

Von Karman Institute for Fluid Dynamics, Rhode Saint Genèse, Belgium

Paper No. 85-GT-108, pp. V001T03A031; 7 pages
  • ASME 1985 International Gas Turbine Conference and Exhibit
  • Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
  • Houston, Texas, USA, March 18–21, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7938-2
  • Copyright © 1985 by ASME


This paper describes the numerical investigation of the three dimensional flow through a low speed, low aspect ratio, high turning annular turbine nozzle guide vane with meridional tip endwall contouring. This rotational flow field has been simulated using a finite volume discretization and a time marching technique to solve the three dimensional, time dependent Euler equations expressed in a cylindrical coordinates system. The results are presented under the form of contour plots, spanwise pitch-averaged distributions and blade static pressure distributions. Detailed comparisons with the measurements described in part I of the paper are also provided.

Copyright © 1985 by ASME
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