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Analysis of Fuel Vaporization, Fuel-Air Mixing, and Combustion in Integrated Mixer-Flame HoldersRequirements to limit pollutant emissions from the gas turbine engines for the future High-Speed Civil Transport (HSCT) have led to consideration of various low-emission combustor concepts. One such concept is the Integrated Mixer-Flame Holder (IMFH). This report describes a series of IMFH analyses performed with KIVA-II, a multi-dimensional CFD code for problems involving sprays, turbulence, and combustion. To meet the needs of this study, KIVA-II's boundary condition and chemistry treatments are modified. The study itself examines the relationships between fuel vaporization, fuel-air mixing, and combustion. Parameters being considered include: mixer tube diameter, mixer tube length, mixer tube geometry (converging-diverging versus straight walls), air inlet velocity, air inlet swirl angle, secondary air injection (dilution holes), fuel injection velocity, fuel injection angle, number of fuel injection ports, fuel spray cone angle, and fuel droplet size. Cases are run with and without combustion to examine the variations in fuel-air mixing and potential for flashback due to the above parameters. The degree of fuel-air mixing is judged by comparing average, minimum, and maximum fuel/air ratios at the exit of the mixer tube, while flame stability is monitored by following the location of the flame front as the solution progresses from ignition to steady state. Results indicate that fuel-air mixing can be enhanced by a variety of means, the best being a combination of air inlet swirl and a converging-diverging mixer tube geometry. With the IMFH configuration utilized in the present study, flashback becomes more common as the mixer tube diameter is increased and is instigated by disturbances associated with the dilution hole flow.
Document ID
20040087138
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Deur, J. M. (NYMA, Inc. Brook Park, OH, United States)
Cline, M. C. (Los Alamos National Lab. NM, United States)
Date Acquired
September 7, 2013
Publication Date
July 1, 2004
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-14610
NASA/CR-2004-213116
Funding Number(s)
CONTRACT_GRANT: NAS3-27235
WBS: WBS 714-09-46
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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