Transient Plasma Ignition of Hydrocarbon-Air Mixtures
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Authors
Wang, F.
Jiang, C.
Kuthi, A.
Gundersen, M.A.
Sinibaldi, C. Brophy and J.0.
Lee, L.C.
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Date of Issue
2004-01
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Publisher
AIAA
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Abstract
A transient plasma ignition system has been demonstrated to substantially reduce the ignition delay and detonation-to-detonation transition times for ethylene-air and propane-air mixtures under dynamic fill conditions. The effects initial conditions including equivalence ratio, a temperature range of 280K to 430K, and pressure range of 1 to 6 atm were evaluated. Ignition delays were reduced by up to a factor of 5 and the correspondingdeflagration-to-detonationtime scales were observed to decrease accordingly when compared to conventional capacitive dischargesystems. Thesubstantialreductionoftheignitiondelaytimesresultedinthegeneration of strong pressure waves which inherently steepened into shock waves quickly and in a short distance. Although direct initiation of a detonation wave was not obtained, the sub sequential use of a Shchelkin spiral was able to rapidly and reliably accelerate the combustion driven shock waves to detonations within practical distances. The efficiency and performance of the transient plasma ignition strategy will likely contribute to the development of fuel-air detonation initiators.
Type
Conference Paper
Description
42nd AIAA Aerospace Sciences Meeting and Exhibit AIAA 2004-834 5 - 8 January 2004, Reno, Nevada
The article of record as published may be found at http://dx.doi.org10.2514/6.2004-834
The article of record as published may be found at http://dx.doi.org10.2514/6.2004-834
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Aeronautics and Astronautics
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Naval Postgraduate School (U.S.)
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.