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Modeling of Tip Clearance Flows Through an Improved 3-D Pressure Correction Navier-Stokes Solver PUBLIC ACCESS

[+] Author Affiliations
N. Lymberopoulos, K. Giannakoglou, I. Nikolaou, K. D. Papailiou

National Technical University of Athens, Athens, Greece

A. Tourlidakis, R. L. Elder

Cranfield Institute of Technology, Cranfield, UK

Paper No. 93-GT-374, pp. V03CT17A035; 12 pages
doi:10.1115/93-GT-374
From:
  • ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 3C: General
  • Cincinnati, Ohio, USA, May 24–27, 1993
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7892-7
  • Copyright © 1993 by ASME

abstract

Mechanical constraints dictate the existence of tip clearances in rotating cascades, resulting to a flow leakage through this clearance which considerably influences the efficiency and range of operation of the machine. Three-dimensional Navier-Stokes solvers are often used for the numerical study of compressor and turbine stages with tip-clearance. The quality of numerical predictions depends strongly on how accurately the blade tip region is modelled; in this respect the accurate modelling of tip region was one of the main goals of this work. In the present paper, a 3-D Navier-Stokes solver is suitably adapted so that the flat tip surface of a blade and its sharp edges could be accurately modelled, in order to improve the precision of the calculation in the tip region. The adapted code solves the fully elliptic, steady, Navier-Stokes equations through a space-marching algorithm and a pressure correction technique; the H-type topology is retained, even in cases with thick leading edges where a special treatment is introduced herein. The analysis is applied to two different cases, a linear cascade and a compressor rotor, and comparisons with experimental data are provided.

Copyright © 1993 by ASME
This article is only available in the PDF format.

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