Model and igniter development for plasma assisted combustion

Skip Williams, Svetozar Popovic, Leposava Vuskovic, Campbell D. Carter, Lance Jacobson, Spencer Kuo, Daniel Bivolaru, Shehan A.P. Corera, Moshan S.P. Kahandawala, Sukh S. Sidhu

Research output: Contribution to conferencePaper

Abstract

Recent progress on our efforts to develop a detailed kinetic mechanism for C 8H m hydrocarbons and practical plasma igniters for plasma-assisted combustion are discussed. Shock tube validation experiments made in argon using a fixed stoichiometry (Φ = 1.0), pressures of approximately 0.95 and 1.05 atm, and temperatures ranging from 850 to 1200 K (post reflected shock) are presented. The mechanism is being expanded to include electron kinetics and to allow for a degree of nonequilibrium modeled with separate electron and gas temperatures. Quantum calculations used to derive needed electron impact ionization/dissociation cross-sections for hydrocarbons are discussed. In addition, ignition of ethylene fuel in a Mach 2 supersonic flow with a total temperature of 590 K and pressure of 5.4 atm is demonstrated using a low frequency discharge with peak and average powers reaching 8 kW and 2.8 kW, respectively.

Original languageEnglish (US)
Pages12375-12384
Number of pages10
StatePublished - 2004
Event42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 5 2004Jan 8 2004

Other

Other42nd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/5/041/8/04

ASJC Scopus subject areas

  • Engineering(all)

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    Williams, S., Popovic, S., Vuskovic, L., Carter, C. D., Jacobson, L., Kuo, S., Bivolaru, D., Corera, S. A. P., Kahandawala, M. S. P., & Sidhu, S. S. (2004). Model and igniter development for plasma assisted combustion. 12375-12384. Paper presented at 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States.