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Stage-by-Stage Dynamic Compression System Modeling for Split Core and Bypass Systems FREE

[+] Author Affiliations
Jules W. Lindau

NASA Lewis Research Center, Cleveland, OH

Walter F. O’Brien

Virginia Polytechnic Institute and State University, Blacksburg, VA

Paper No. 96-GT-279, pp. V005T16A015; 15 pages
doi:10.1115/96-GT-279
From:
  • ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; General
  • Birmingham, UK, June 10–13, 1996
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7876-7
  • Copyright © 1996 by ASME

abstract

A method for solving a set of equations for one-dimensional stage-by-stage dynamic compression system modeling was applied to a two-dimensional post-stall model. The model is suitable for capturing the flow during surge in split flow systems such as tuibofans and, possibly, in centrifugal compressors. The modeling requires the solution of a modified form of the Euler equations in axisymmetric form. A robust solution method was facilitated by the use of a special form of upwind flux, flux difference splitting with source terms (FDSS), and implicit time integration. The modeling method was applied to the simulation of a split flow-path fan system and results are presented.

Copyright © 1996 by ASME
Topics: Modeling , Compression
This article is only available in the PDF format.

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