Title: Design of a High Turbulence Intensity Combustion System
Abstract: Arturo Acosta-Zamora, Arif Hossain, Marco Quiroz, Ahsan Choudhuri, PhD NASA Center for Space Exploration Technology Research (cSETR) Department of Mechanical Engineering University of Texas at El Paso El Paso, Texas, 79968-0521 E-mail:[email protected] The design of a combustion system for flow in compressible, turbulent, and premixed conditions is hereby presented. An air-methane mix has been selected as the basis for this study where the system is composed of three main subsystems: the air handling and preparation, instrumentation and controls, and the combustor. A backward-facing step flame stabilization method and optical accessibility features for flow diagnostics were the main drivers for the combustor design, which was sized for compressible flow (M > 0.3), and a maximum operating pressure of 6 bar. A grid, or perforated plate, of different hole diameters and blockage ratios will be used as the turbulence generator for the experiment. Optical access to the chamber is provided via the use of quartz windows on three sides of the square chamber. In order to increase the inlet temperature of the air, a heating section was designed to use commercially available in-line heaters. Finally, a LabVIEW software interface has been selected as the control mechanism for the experimental setup. Preliminary understanding of the flow field inside the combustor was achieved through the use of Large Eddy Simulation (LES) analyses for fluid flow and Finite Element Analysis (FEA) for structural integrity. Preliminary PIV integration analysis has been conducted with a prototype polycarbonate model of the combustor flow path.
Publication Year: 2014
Publication Date: 2014-07-25
Language: en
Type: article
Indexed In: ['crossref']
Access and Citation
Cited By Count: 3
AI Researcher Chatbot
Get quick answers to your questions about the article from our AI researcher chatbot