RESEARCH PAPERS: Gas Turbines: Combustion & Fuels

A Comprehensive Model to Predict Simplex Atomizer Performance

[+] Author and Article Information
Y. Liao, S. M. Jeng

Department of Aerospace Engineering, University of Cincinnati, Cincinnati, OH 45221

A. T. Sakman, M. A. Jog

Department of Mechanical Engineering, University of Cincinnati, Cincinnati, OH 45221

M. A. Benjamin

Gas Turbine Fuel Systems Division, Parker Hannifin Corporation, Mentor, OH 44060

J. Eng. Gas Turbines Power 121(2), 285-294 (Apr 01, 1999) (10 pages) doi:10.1115/1.2817119 History: Received June 30, 1998; Revised February 10, 1999; Online December 03, 2007


The pressure swirl atomizer, or simplex atomizer, is widely used in liquid fuel combustion devices in the aerospace and power generation industries. A computational, experimental, and theoretical study was conducted to predict its performance. The Arbitrary-Lagrangian-Eulerian method with a finite-volume scheme is employed in the CFD model. Internal flow characteristics of the simplex atomizer, as well as its performance parameters such as discharge coefficient, spray angle and film thickness, are predicted. A temporal linear stability analysis is performed for cylindrical liquid sheets under three-dimensional disturbances. The model incorporates the swirling velocity component, finite film thickness and radius that are essential features of conical liquid sheets emanating from simplex atomizers. It is observed that the relative velocity between the liquid and gas phases, density ratio and surface curvature enhance the interfacial aerodynamic instability. The combination of axial and swirling velocity components is more effective than only the axial component for disintegration of liquid sheet. For both large and small-scale fuel nozzles, mean droplet sizes are predicted based on the linear stability analysis and the proposed breakup model. The predictions agree well with experimental data at both large and small scale.

Copyright © 1999 by The American Society of Mechanical Engineers
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