Effects of thermally cracked component of n-dodecane on supersonic combustion behaviors in a scramjet model combustor

Nakaya, Shinji; Tsue, Mitsuhiro; Kono, Michikata; Imamura, Osamu; Tomioka, Sadatake

doi:10.1016/j.combustflame.2015.07.021

Cited by 37 publications

(8 citation statements)

References 29 publications

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“…Providing some references for the simulation modeling and energy optimization design of cooling channels for future propulsion systems, this series of studies possesses the potential to further exploration on how to improve energy conversion and ignition efficiency through optimizing physical parameters of thermal management. Nakaya et al [84] investigated how the pyrolysis components of n-dodecane affect the combustion behavior of the fuel with the experimental setup shown in Figure 22. With universal applicability to other hydrocarbon fuels, this method has certain value in system fuel selection.…”

Section: Low-temperature Systemsmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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Section: Low-temperature Systemsmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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“…11) For example, because the larger liquid parent fuel decomposes into smaller gaseous hydrocarbons at high temperature, it is anticipated that these changes in the fuel state or chemical composition will significantly alter the fuel injection behavior and the subsequent ignition and combustion process. 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).…”

Section: Introductionmentioning

confidence: 99%

“…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 ). 14) Fan et al conducted an autoignition test of cracked kerosene in a Mach 2.5 model combustor using a range of fuel injection conditions and varying amounts of pilot hydrogen. 12) From the experimental results, they indicated that the amount of pilot hydrogen required for achieving autoignition decreased as the extent of kerosene cracking increased.…”

Section: Introductionmentioning

confidence: 99%

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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“…For hypersonic flying vehicles, Endothermic hydrocarbon fuel has been widely considered to be used as the propellant and coolant for thermal protection 1‐4 . The fuel experiences thermal decomposition in the heat exchanger of flow channels to produce small hydrocarbon species and hydrogen 5‐7 . The cracked products mainly consist of liquid and gaseous components 8,9 .…”

Section: Introductionmentioning

confidence: 99%

Experimental study of ignition behaviors of pyrolysis gas of kerosene‐based endothermic hydrocarbon fuel

2021

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Summary The pyrolysis gas consisting of 29.4% CH4, 21.3% C2H4, 30.8% C2H6, and 18.5% C3H6 in mole fraction is presented, as the surrogate of the actual gaseous pyrolysis products. At the conditions of TC = 877.7‐963 K, PC = 3.22‐4.37 MPa, φ = 0.5 and 1.0, the ignition delays of pyrolysis gas/air (diluted with 52% Ar) have been measured. With TC or PC increasing, the ignition delay time decreases. The auto‐ignition of φ = 1.0 is faster than that of φ = 0.5. Furthermore, two widely used small hydrocarbons chemical mechanisms are validated with the measured results. The USC‐II mechanism can well predict experimental results at high‐T regimes, but fails at low‐T regimes. By sensitivity analysis of temperature, the two elementary reactions C2H6 + OH = C2H5 + H2O (negative sensitivity coefficient) and C3H6 + OH = aC3H5 + H2O (positive sensitivity coefficient) have been identified, which have higher reactivity at low‐T and lower reactivity at high‐T. Considering the extreme uncertainty of rate constants of C3H6 + OH = aC3H5 + H2O, the kinetic parameters have been modified for improving the predictions. The validated results indicate that the optimized mechanism improves predictions of the auto‐ignition behavior at low temperature regimes.

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Effects of thermally cracked component of n-dodecane on supersonic combustion behaviors in a scramjet model combustor

Cited by 37 publications

References 29 publications

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

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

Experimental study of ignition behaviors of pyrolysis gas of kerosene‐based endothermic hydrocarbon fuel

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