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

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

Electrical and Computer Engineering

Research output: Contribution to conference › Paper › peer-review

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 language	English (US)
Pages	12375-12384
Number of pages	10
State	Published - 2004
Event	42nd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States Duration: Jan 5 2004 → Jan 8 2004

Other

Other	42nd AIAA Aerospace Sciences Meeting and Exhibit
Country/Territory	United States
City	Reno, NV
Period	1/5/04 → 1/8/04

ASJC Scopus subject areas

General Engineering

Cite this

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title = "Model and igniter development for plasma assisted combustion",

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.",

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

year = "2004",

language = "English (US)",

pages = "12375--12384",

note = "42nd AIAA Aerospace Sciences Meeting and Exhibit ; Conference date: 05-01-2004 Through 08-01-2004",

}

TY - CONF

T1 - Model and igniter development for plasma assisted combustion

AU - Williams, Skip

AU - Popovic, Svetozar

AU - Vuskovic, Leposava

AU - Carter, Campbell D.

AU - Jacobson, Lance

AU - Kuo, Spencer

AU - Bivolaru, Daniel

AU - Corera, Shehan A.P.

AU - Kahandawala, Moshan S.P.

AU - Sidhu, Sukh S.

PY - 2004

Y1 - 2004

N2 - 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.

AB - 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.

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M3 - Paper

AN - SCOPUS:2942726312

SP - 12375

EP - 12384

T2 - 42nd AIAA Aerospace Sciences Meeting and Exhibit

Y2 - 5 January 2004 through 8 January 2004

ER -

Model and igniter development for plasma assisted combustion

Abstract

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ASJC Scopus subject areas

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