A pulsed plasma torch and its performance in a Mach 2.5 supersonic flow

Spencer P. Kuo; Daniel Bivolaru

doi:10.1109/TPS.2005.863596

A pulsed plasma torch and its performance in a Mach 2.5 supersonic flow

Spencer P. Kuo, Daniel Bivolaru

Electrical and Computer Engineering

Research output: Contribution to journal › Article › peer-review

Abstract

Characteristics of torch plasma that is intended as an ignition aid within a scramjet engine are studied in a Mach 2.5 wind tunnel. This torch system, with its high-voltage discharge between the electrodes of a torch module, is operated in pulsed mode. The plasma jet generated by this torch module is diagnosed by the discharge power and through imaging of its plume in a quiescent environment and in a supersonic crossflow. This torch can deliver up to 100 J in each pulse. Within the Mach-2.5 supersonic flow, which approximates the scramjet-engine startup condition, the penetration height and the volume of torch plume into the crossflow are determined.

Original language	English (US)
Pages (from-to)	63-69
Number of pages	7
Journal	IEEE Transactions on Plasma Science
Volume	34
Issue number	1
DOIs	https://doi.org/10.1109/TPS.2005.863596
State	Published - Feb 2006

Keywords

Ignition aid
Plasma torch
Scramjet
Supersonic combustor

ASJC Scopus subject areas

Nuclear and High Energy Physics
Condensed Matter Physics

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10.1109/TPS.2005.863596

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title = "A pulsed plasma torch and its performance in a Mach 2.5 supersonic flow",

abstract = "Characteristics of torch plasma that is intended as an ignition aid within a scramjet engine are studied in a Mach 2.5 wind tunnel. This torch system, with its high-voltage discharge between the electrodes of a torch module, is operated in pulsed mode. The plasma jet generated by this torch module is diagnosed by the discharge power and through imaging of its plume in a quiescent environment and in a supersonic crossflow. This torch can deliver up to 100 J in each pulse. Within the Mach-2.5 supersonic flow, which approximates the scramjet-engine startup condition, the penetration height and the volume of torch plume into the crossflow are determined.",

keywords = "Ignition aid, Plasma torch, Scramjet, Supersonic combustor",

author = "Kuo, {Spencer P.} and Daniel Bivolaru",

note = "Funding Information: Manuscript received September 26, 2004; revised November 19, 2005. This work was supported by Air Force Office of Scientific Research (AFOSR) under Grant AFOSR-FA9550-04-1-0352. S. P. Kuo is with the Department of Electrical and Computer Engineering, Polytechnic University, Brooklyn, NY 11201 USA. D. Bivolaru was with the Department of Electrical and Computer Engineering, Polytechnic University, Brooklyn, NY 11201 USA. He is now with the NASA Langley Research Center, Hampton, VA 23681-2199 USA. Digital Object Identifier 10.1109/TPS.2005.863596",

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AU - Bivolaru, Daniel

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N2 - Characteristics of torch plasma that is intended as an ignition aid within a scramjet engine are studied in a Mach 2.5 wind tunnel. This torch system, with its high-voltage discharge between the electrodes of a torch module, is operated in pulsed mode. The plasma jet generated by this torch module is diagnosed by the discharge power and through imaging of its plume in a quiescent environment and in a supersonic crossflow. This torch can deliver up to 100 J in each pulse. Within the Mach-2.5 supersonic flow, which approximates the scramjet-engine startup condition, the penetration height and the volume of torch plume into the crossflow are determined.

AB - Characteristics of torch plasma that is intended as an ignition aid within a scramjet engine are studied in a Mach 2.5 wind tunnel. This torch system, with its high-voltage discharge between the electrodes of a torch module, is operated in pulsed mode. The plasma jet generated by this torch module is diagnosed by the discharge power and through imaging of its plume in a quiescent environment and in a supersonic crossflow. This torch can deliver up to 100 J in each pulse. Within the Mach-2.5 supersonic flow, which approximates the scramjet-engine startup condition, the penetration height and the volume of torch plume into the crossflow are determined.

KW - Ignition aid

KW - Plasma torch

KW - Scramjet

KW - Supersonic combustor

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A pulsed plasma torch and its performance in a Mach 2.5 supersonic flow

Abstract

Keywords

ASJC Scopus subject areas

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