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Multi-Blade Row Navier-Stokes Simulations of Fan-Bypass Configurations PUBLIC ACCESS

[+] Author Affiliations
W. N. Dawes

Whittle Laboratory, Cambridge, UK

Paper No. 91-GT-148, pp. V001T01A060; 7 pages
doi:10.1115/91-GT-148
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7898-9
  • Copyright © 1991 by ASME

abstract

This paper describes extensions to a multi-blade row 3D Navier-Stokes solver to enable fan-splitter-bypass geometries to be handled. The code is applied to two generic configurations. The core-bypass splitter can exert considerable upstream influence via its associated pressure field and in the example shown here severely disturbs the fan suction surface boundary layer. The behaviour of the bypass ogv is substantially modified both by the clearance flow of the upstream fan and also by thicker than expected boundary layers on the splitter upper surface caused by the splitter LE incidence associated with the particular bypass ratio selected for the example.

Copyright © 1991 by ASME
This article is only available in the PDF format.

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