An improved aerodynamic ramp injector in supersonic flow

Jacobsen, Lance; Gallimore, S. D.; Schetz, Joseph A.; O’Brien, Walter F.

doi:10.2514/6.2001-518

Cited by 23 publications

(13 citation statements)

References 13 publications

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“…Jacobsen, et al [72] commented that the "sheltered channel" created within the wake of the aero-ramp injector jets as noticed by Schetz, et al [69] could be incorporated with plasma torch igniter. This sheltered channel could act as a suitable region for flame initiation and rapid spreading into the jet plume [72].…”

Section: Pylon Injectorsmentioning

confidence: 99%

See 1 more Smart Citation

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Section: Pylon Injectorsmentioning

confidence: 99%

“…This sheltered channel could act as a suitable region for flame initiation and rapid spreading into the jet plume [72].…”

Section: Pylon Injectorsmentioning

confidence: 99%

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Tourani

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…The wide variety of research at Virginia Tech has contributed to the development of plasma-assisted ignition and combustion in high-speed flows over the years. A summary of plasma-assisted combustion research conducted at Virginia Tech [39][40][41][42][43][44][45][46][47][48] is shown in Table 2.2.…”

Section: Plasma-assisted Combustionmentioning

confidence: 99%

Plasma Torch Atomizer-Igniter for Supersonic Combustion of Liquid Hydrocarbon Fuels

Billingsley¹,

O’Brien²,

Schetz³

2006

14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

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To realize supersonic combustion of hydrocarbons, an effective atomizer-igniter combination with the capabilities of fuel preheating, atomization, penetration, mixing, ignition and flameholding is desired. An original design concept incorporating these capabilities was built and tested at Virginia Tech, and was found to provide good penetration, effective atomization, and robust ignition and flameholding. Quiescent testing with kerosene and JP-7 provided initial performance data. The atomizer-injector design was then modified for insertion In the quiescent environment, the regeneratively cooled plasma torch igniter was found to significantly increase electrode life while heating, atomizing, and igniting the liquid fuel. Jet breakup length was measured and characterized, and mean droplet size was estimated using an existing correlation. Several qualitative observations regarding quiescent combustion were made, including torch power effects and the process of flame formation. In the supersonic environment, the effect of fuel injection direction was analyzed. Best results were obtained when fuel was injected with a velocity component opposite to the direction of main tunnel flow. Repeatable ignition occurred in the supersonic boundary layer at the fuel stagnation location near the plasma torch plume. Direct, filtered, shadowgraph, and schlieren photographs, temperature ii measurements, and visible emission spectroscopy provided evidence of combustion and the details of the flame structure.The new atomizer-igniter design provided robust and reliable ignition and flameholding of liquid hydrocarbon fuels in an unheated supersonic flow at M=2.4, with no ramp, step, or other physical penetration into the flowpath.iii Acknowledgements Dr. O'Brien, I enjoyed the relaxed lab atmosphere, and am grateful for your unique ability to promote progress without being overbearing. Thank you for recognizing my circumstances, and being flexible as I managed my young family. Thank you for the enthusiasm you show for your research; it was a privilege and a joy working with you.

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“…Aiming at rapid mixing of fuel with supersonic crossflow, transverse jet [2][3][4], ramp jet [5,6], aerodynamic ramp jet [7,8], pylon jet [9,10] and strut jet [11] have been investigated in experiment and numerical simulations extensively. Among these injection schemes, the transverse fuel injection through a wall orifice has been proved to be one of the simplest and most conventional methods for the scramjet engine.…”

Section: Introductionmentioning

confidence: 99%

Effects of oblique and transverse injection on the characteristics of jet in supersonic crossflow

2015

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An improved aerodynamic ramp injector in supersonic flow

Cited by 23 publications

References 13 publications

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Computational Simulation of Scramjet Combustors - A Comparison between Quasi-One Dimensional and 2-D Numerical Simulations

Plasma Torch Atomizer-Igniter for Supersonic Combustion of Liquid Hydrocarbon Fuels

Effects of oblique and transverse injection on the characteristics of jet in supersonic crossflow

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