RESEARCH PAPERS: Gas Turbines: Aircraft

A Computational Model for the Study of Gas Turbine Combustor Dynamics

[+] Author and Article Information
D. M. Costura, P. B. Lawless, S. H. Fankel

Thermal Science and Propulsion Center, School of Mechanical Engineering, Purdue University, 1003 Chaffee Hall, West Lafayette, IN 47907-1003

J. Eng. Gas Turbines Power 121(2), 243-248 (Apr 01, 1999) (6 pages) doi:10.1115/1.2817112 History: Received April 01, 1998; Online December 03, 2007


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 © 1999 by The American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In