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RESEARCH PAPERS: Gas Turbines: Combustion and Fuels

A Semi-Analytical Finite Rate Two-Reactor Model for Gas Turbine Combustors

[+] Author and Article Information
J. H. Tonouchi

Analytic and Computational Research, Inc. Cincinnati, OH

T. J. Held, H. C. Mongia

General Electric Aircraft Engines Company, Combustion Center of Excellence, Cincinnati, OH

J. Eng. Gas Turbines Power 120(3), 495-501 (Jul 01, 1998) (7 pages) doi:10.1115/1.2818172 History: Received March 01, 1997; Online November 19, 2007

Abstract

A gas turbine combustor is modeled using a two-reactor, finite-rate mixing and chemistry gas particle approach. The first reactor, used to simulate combustion in the primary zone, permits independent definition of the rates of macromixing and micromixing within the reactor, and the amount of premixing of fuel and air entering the reactor. Finite-rate macromixing is simulated by consideration of the fluid particle residence time distribution frequency function and the ages of the particles in the reactor. Finite-rate micromixing is simulated using a modified Coalescence-Dispersion (C-D) model. The second reactor model simulates combustion in the dilution zone of the combustor, and is modeled as a plug flow reactor with cross-flowing jets of dilution air and co-flowing streams of cooling film air. The primary zone reactor model predicts physically reasonable trends in mean temperature, and CO and NOx emissions as the macromixing and micromixing parameters are varied with respect to the perfectly stirred reactor limit. The model also has shown to predict the correct trends in modeling NOx and CO emissions from aircraft engine gas turbine combustors.

Copyright © 1998 by The American Society of Mechanical Engineers
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