Ignition Characteristics of Plasma Torch for Hydrogen Jet in an Airstream

Takita, Kenichi; Uemoto, Tomokazu; Sato, Takahiro; Ju, Yiguang; Masuya, Goro; Ohwaki, Katsura

doi:10.2514/2.5587

Cited by 52 publications

(17 citation statements)

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“…Thus, it is of great importance to accelerate the combustion to ensure full heat release and stable combustion under such a hostile condition [2], especially at low Mach number flight condition, where ignition is the most critical problem for combustor design due to the low stagnation temperature [14,16]. To overcome the ignition difficulty in supersonic flow, application of both thermo-equilibrium and non-equilibrium plasma to supersonic combustion has become an active research field in recent years [5,11,13,22,27,30]. The plasma can not only facilitate the easy ignition of fuel/air mixture but also the acceleration of combustion process, which are crucial for the sustainability of stable combustion in supersonic free stream.…”

Section: Introductionmentioning

confidence: 99%

“…Thermo-equilibrium plasma generator, the plasma jet (PJ) torch, contains large amount of radicals in the high temperature plasma gas and enjoys several potential advantages for combustion enhancement as a supersonic igniter [8,9,11,15,24,27]. The former studies mostly focused on the effects of feedstock [15,19,21], location of fuel injector [9] and airflow parameters on ignition characteristics for both hydrogen and hydrocarbon fuels.…”

Section: Introductionmentioning

confidence: 99%

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Plasma-assisted ignition for a kerosene fueled scramjet at Mach 1.8

Tong

et al. 2013

Aerospace Science and Technology

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By using a plasma jet (PJ) torch with 1.5 kW input power as an igniter, successful ignition for liquidkerosene fueled combustion experiment was conducted in a direct-connected supersonic test facility. The incoming flow has total temperature of 950 K and local Mach number of 1.8, corresponding to Mach 4 flight condition. In this study, several optical techniques, including high speed photography, high speed schlieren photography, and planar laser scattering (PLS) technique, were combined to study the ignition process, flame propagation, and mixing features of liquid kerosene fuel with air around the cavity. The effect of fuel injection position, injection pressure, and feedstock gas on ignition performance has been analyzed. The results indicate that local mixing is a critical factor for ignition. It is also shown that the PJ torch with N 2 + H 2 feedstock is superior to the PJ torch with N 2 feedstock for the ignition of liquidkerosene fuel. These results are valuable for the future optimization of kerosene-fueled scramjet engine when using a PJ torch as an igniter.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Plasma-assisted ignition for a kerosene fueled scramjet at Mach 1.8

Tong

et al. 2013

Aerospace Science and Technology

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“…The measured time delays of the ignition of the H 2 -air-Ar mixture are shown in Figure 4. 13. At T = 1000 K, the energy input in the discharge decreases the ignition delay time by a factor of 4.8, from 860 to 140 µs.…”

Section: Ignition Delay Time Change In H 2 -O 2 Mixture By Pulsed Dismentioning

confidence: 99%

“…6. 13. The main fraction of the pulse energy goes to the dissociation and electronic excitation of molecules (in particular, nitrogen molecules).…”

Section: Electron-impact Excitation Of Molecules In a Barrier Dischargementioning

confidence: 99%

“…The most typical geometrical configuration includes a turboblower with a special system of fuel injection and a plasma torch system where one of the electrodes is a metallic nozzle. In this case, ignition limits strongly depend on the system geometry, for example, on the location of the plasma torch in relation to the fuel injectors, on the penetration height of the plasma torch, which is in inverse proportion to flow velocity, 13 etc. In spite of the presence of different ignition methods, the problem of a fast and homogeneous ignition of a combustible mixture remains topical.…”

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confidence: 99%

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Plasma-assisted combustion

Starikovskii

Anikin

Kosarev

et al. 2006

Pure and Applied Chemistry

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information , 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)12-03-2007 REPORT TYPE Final Report DATES COVERED (From -To AUTHOR(S)Professor Andrei Y Starikovskii 5e. WORK UNIT NUMBER PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)Moscow Institute of Physics and Technology 9 Institutski Lane Dolgoprudny 141700 Russia PERFORMING ORGANIZATION REPORT NUMBERN/A SPONSOR/MONITOR'S ACRONYM(S) 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)EOARD PSC 821 BOX 14 FPO AE 09421-0014 SPONSOR/MONITOR'S REPORT NUMBER(S)CRDF 02-9003 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThis report results from a contract tasking Moscow Institute of Physics and Technology as follows: The contractor will investigate the use of high voltage, nano-second plasma discharges to ignite and efficiently combust fuel/air mixtures in high speed flows. This strongly nonequilibrium low-temperature plasma has a high mean energy of electrons and will provide a source of reactive atoms, radicals, and excited molecules which has been shown to enhance ignition and combustion. The short duration of the pulses results in relatively low power requirements for generating the discharge. The goal is to demonstrate and understand the physics of energy exchange, ignition and combustion . Also, the use of this type of plasma for aerodynamic flow control will be investigated. Finally, applicability to use this type of discharge to directly initiate a detonation wave will be investigated. Chapter 1 SUBJECT TERMS AbstractA review was made which discusses different types of the discharges applied for plasma assisted ignition and combustion. Special attention to experimental and theoretical analysis of some plasma parameters was given, such as reduced electric field, electron density and energy branching for different gas discharges. Streamers, pulsed nanosecond discharges, dielectric barrier discharges, radio frequency discharges, atmospheric pressure glow discharges are considered. Detailed measurements of the parameters of a streamer flash development in the air for the pressure range 90-1300 Torr have been carried out in the plane-to-plane geometry for 20-42 ...

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Plasma-Assisted Hydrogen Combustion

Mao

Lefkowitz

et al. 2023

Green Energy and Technology

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Ignition Characteristics of Plasma Torch for Hydrogen Jet in an Airstream

Cited by 52 publications

References 12 publications

Plasma-assisted ignition for a kerosene fueled scramjet at Mach 1.8

Plasma-assisted ignition for a kerosene fueled scramjet at Mach 1.8

Plasma-assisted combustion

Plasma-Assisted Hydrogen Combustion

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