A Dual-Mode Scramjet Combustor employing a Jet Fuel for Hypersonic Flight Vehicle

Nakayama, Hisahiro; Edanaga, Takayuki; Hashino, Seiki; Tomioka, Sadatake; Kobayashi, Kan; Takahashi, Masahiro

doi:10.2514/6.2018-4452

Cited by 2 publications

(3 citation statements)

References 8 publications

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“…35) In the combustion experiment of scramjet mode operation using jet fuel, a peak in the wall pressure was observed around the aft end of the cavity; hence, it was deduced that the exothermic chemical reaction peaked. 15) The cavity residence time ( res cavity was estimated based on the model of Davis and Bowersox. 36) It was derived using the cavity depth D and the velocity of the main flow U,…”

Section: Cavity Internal Flow Conditionsmentioning

confidence: 99%

“…12,13) Previous research investigated the supersonic combustion of hydrocarbon pyrolysis fuels such as n-dodecane, 14) kerosene, 12) and jet fuel. 15) Nakaya et al evaluated the supersonic combustion of a surrogate fuel of the n-dodecane pyrolysis fuel which had four components (i.e., hydrogen, methane, ethane, and ethylene). Moreover, they investigated the combustion effect of adding hydrogen, methane, and ethylene to basic fuel 1 (6% H 2 /29% CH 4 /23% C 2 H 6 /41% C 2 H 4 ).…”

Section: Introductionmentioning

confidence: 99%

“…From the experimental results, in the scramjet mode, although the fuel cracking rates in the tests-firings were different, the wall pressure distributions were almost identical. 15) However, they indicated that the influence of fuel cracking on the combustion characteristics could not be investigated quantitatively, and the investigation was limited to a qualitative discussion. 15) The detailed ignition characteristics of all pyrolysis components were not clarified because previous research had only been carried out to investigate pyrolysis gas components.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Study on the Ignition Method for n-Octane Pyrolysis Fuel in a Scramjet Engine

Ogawa

Kobayashi

Tomioka

2022

Trans. Japan Soc. Aero. S Sci.

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In scramjet engines, ignition must take place within a residence time on the order of milliseconds. In this study, secure ignition conditions for specified n-octane pyrolysis fuel components used in autoignition or forced-ignition by plasma jet torch in a high-speed flow were numerically investigated. First, the ignition delay time within the combustor and cavity flame-holder was estimated using chemical reaction analysis. Three fuel components (n-C 8 H 18 , all pyrolysis fuel (15 components, decomposition rate under 11%)), and pyrolysis gas fuel (eight gas fuel components, decomposition rate under 11%) could not self-ignite within the combustor and cavity residence time. Secondly, ignition using a plasma jet torch in the cavity was numerically investigated. In the case of forced-ignition by plasma jet torch, all pyrolysis fuel (No. 3) and n-C 8 H 18 could ignite within the cavity residence time with less input energy than pyrolysis gas fuel (No. 3) under three kinds of Mach number flight conditions (M 0 = 4, 6, and 8). Moreover, the effect of shortening the ignition delay time by raising the plasma jet torch gas temperature and O radical rate within the cavity was investigated. Ignition of the three kinds of mixture fuel was more greatly affected by the torch injection temperature than the O radical rate in the cavity under all Mach number flight conditions.

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Section: Cavity Internal Flow Conditionsmentioning

confidence: 99%