Abstract
Combustion simulations of H2-O2 ignition are presented here, with a self-consistent plasma uid model for ignition initiation. The plasma uid equations for a nanosecond pulsed discharge are solved and coupled with the governing equations of combustion. The discharge operates with the propagation of cathode directed streamer, with radical species produced at streamer heads. These radical species play an important role in the ignition process. The streamer propagation speeds and radical production rates were found to be sensitive to gas temperature and fuel-oxidizer equivalence ratio. The oxygen radical production rates strongly depend on equivalence ratio and subsequently results in faster ignition of leaner mixtures.
Original language | American English |
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Number of pages | 14 |
DOIs | |
State | Published - 2016 |
Event | 54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States Duration: 4 Jan 2016 → 8 Jan 2016 |
Conference
Conference | 54th AIAA Aerospace Sciences Meeting, 2016 |
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Country/Territory | United States |
City | San Diego |
Period | 4/01/16 → 8/01/16 |
Bibliographical note
Publisher Copyright:© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.
NREL Publication Number
- NREL/CP-2C00-65851
Other Report Number
- AIAA 2016-2158
Keywords
- combustion simulations
- plasma fluid