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A Computational Model for the Study of Gas Turbine Combustor Dynamics FREE

[+] Author Affiliations
David M. Costura, Patrick B. Lawless, Steven H. Frankel

Purdue University, West Lafayette, IN

Paper No. 98-GT-342, pp. V002T02A007; 8 pages
doi:10.1115/98-GT-342
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7863-7
  • Copyright © 1998 by ASME

abstract

A dynamic combustor model is developed for inclusion into a one-dimensional full gas turbine engine simulation code. A flux-difference splitting algorithm is used to numerically integrate the quasi-one-dimensional Euler equations, supplemented with species mass conservation equations. The combustion model involves a single-step, global finite-rate chemistry scheme with a temperature-dependent activation energy. Source terms are used to account for mass bleed and mass injection, with additional capabilities to handle momentum and energy sources and sinks. Numerical results for cold and reacting flow for a can-type gas turbine combustor are presented. Comparisons with experimental data from this combustor are also made.

Copyright © 1998 by ASME
This article is only available in the PDF format.

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