Stage-by-stage dynamic compression system modeling for split core and bypass systems

Jules Washington V. Lindau, Walter F. O'Brien

Research output: Contribution to journalConference articlepeer-review


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 turbofans 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.

Original languageEnglish (US)
JournalAmerican Society of Mechanical Engineers (Paper)
StatePublished - Jan 1 1996
EventProceedings of the 1996 International Gas Turbine and Aeroengine Congress & Exhibition - Burmingham, UK
Duration: Jun 10 1996Jun 13 1996

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering


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