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A Fast Numerical Procedure to Solve the Meridional Equations of Motion in a Multistage Axial Flow Turbomachine FREE

[+] Author Affiliations
A. Kündig

Sulzer Brothers Ltd., Winterthur, Switzerland

Paper No. 81-GT-133, pp. V002T08A014; 8 pages
doi:10.1115/81-GT-133
From:
  • ASME 1981 International Gas Turbine Conference and Products Show
  • Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations
  • Houston, Texas, USA, March 9–12, 1981
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7962-7
  • Copyright © 1981 by ASME

abstract

A new numerical procedure has been developed to solve the meridional equations of motion in an axial flow turbomachine. It is based on the so-called streamline-curvature method. The primary aim of this project was to reduce the computing-time of existing programs. The procedure has been tested. The new program is coupled with a program for the calculation of end-wall-boundary layers on axial flow compressors. This combination makes the simulation of real flow conditions possible. The pitch wise deviation angles and blade-row efficiencies are generally given as input. For compressor blades of the NACA-65-family they can be called from stored empirical data as function of geometry and the upstream and downstream flow conditions. The paper presents an exact description of the numerical procedure and a computed example.

Copyright © 1981 by ASME
This article is only available in the PDF format.

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