Numerical Study on Combustor Flow-Path Design for a Scramjet Flight Experiment

Takahashi, Masahiro; Tomioka, Sadatake; Kodera, Masatoshi; Kobayashi, Kan; Hasegawa, Susumu; Shimizu, Taro; Aono, Junya; Munakata, Toshihiko

doi:10.2322/tastj.19.415

Cited by 4 publications

(2 citation statements)

References 6 publications

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“…More detail on the combustor configuration is given in Ref. [19]. 3D-RANS simulations were conducted using a JAXA inhouse solver, LS-FLOW, a finite-volume compressible flow solver for arbitrary unstructured grids, originally developed for aerodynamic simulation of an external flow around flying vehicles [20].…”

Section: Validation 3: 3d Reacting Flow Simulationmentioning

confidence: 99%

“…22b and 23b, the error in pressure distribution under facility conditions is comparable with the difference in pressure distribution between flight and facility conditions. In addition, the 19 Acknowledgements The authors would like to acknowledge the contributions of T. Shimizu (Japan Aerospace Exploration Agency), J. Aono (Research Center of Computational Mechanics, Inc.), and T. Munakata (Hitachi Solutions East Japan) for their outstanding support of this work. This work was supported by the Innovative Science and Technology Initiative for Security Grant Number JPJ004596, ATLA, Japan.…”

Section: Validation 3: 3d Reacting Flow Simulationmentioning

confidence: 99%

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Reaction mechanism reduction for ethylene-fueled supersonic combustion CFD

et al. 2023

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CHEMKIN-Pro was used to build a custom-made reduced reaction mechanism for a 3D simulation of C2H4/Air reaction in a supersonic combustion ramjet (scramjet) combustor for the JAXA S-520-RD1 flight test performed on 24 July 2022. It was also attempted to reproduce the effect of unavoidable H2O vitiation in the facility (ground) test on combustion characteristics. USC Mech II (a 111-species mechanism) was applied as the master mechanism. First, 1D simulation was conducted by applying a plug flow reactor model; 34-, 23-, 20-, 18-, and 19-species mechanisms were suggested as candidates for reduced mechanism. Then, 0D ignition delay simulation by applying a perfectly stirred reactor model by CHEMKIN-Pro, 2D reacting flow simulation by CRUNCH CFD, and 3D reacting flow simulation by RANS were performed to select the most suitable reduced mechanism. The 20-species (96-elementary-reactions) mechanism consisted of H2, O2, N2, H2O, CO2, CO, H, O, OH, HO2, CH2, CH2*, CH3, HCO, CH2O, CH3O, C2H2, C2H3, C2H4, and CH2CHO and was selected as the best-reduced reaction mechanism for C2H4-fueled 3D simulation under the flight and facility conditions corresponding to the RD1 flight test.

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Section: Validation 3: 3d Reacting Flow Simulationmentioning

confidence: 99%

Section: Validation 3: 3d Reacting Flow Simulationmentioning

confidence: 99%

Reaction mechanism reduction for ethylene-fueled supersonic combustion CFD

et al. 2023

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An Experimental Investigation on Forced Ignition Characteristics of Hydrocarbon Mixture Fuel in Scramjet Combustor

Ogawa

Kobayashi

Tomioka

2022

Lecture Notes in Electrical Engineering

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Combustion characteristics of a supersonic combustor model for a JAXA flight experiment

2023

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JAXA is conducting a flight-ground test comparison program to clarify the “facility effect” on hypersonic aerodynamics and combustion phenomena and to develop a CFD tool for predicting flight data from ground test data. The aim is a flight experiment to obtain data on aerodynamic heating and supersonic combustion under actual flight conditions and to validate the CFD tool using flight data and the corresponding ground test data. This study aimed at determining a flow-path geometry and a fuel injector configuration for a supersonic combustor suitable for clarifying the influence of the different test flow compositions between flight and ground test conditions on combustion. The candidate configurations proposed by the CFD study were evaluated by direct-connect combustion tests using ethylene fuel. The results showed that a combustor flow was symmetric when the fuel equivalence ratio was low and asymmetric when the equivalence ratio and the pressure in the combustor were high. Because an asymmetric flow is unsuitable for validating CFD based on steady RANS, the total equivalence ratio was limited to 0.44. The combustor model uses two-stage fuel injectors and cavity flame holders to combust ethylene fuel. The depth of the cavity flame holder had little influence on combustion. However, the number of injection holes for the injector located downstream of the cavity affected the combustor pressure. The combustor flow-path design was finalized based on the combustion test results. In addition, an ethylene fuel ignition method using pilot hydrogen injection, adopted for the flight experiment, was also demonstrated successfully.

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Numerical Study on Combustor Flow-Path Design for a Scramjet Flight Experiment

Cited by 4 publications

References 6 publications

Reaction mechanism reduction for ethylene-fueled supersonic combustion CFD

Reaction mechanism reduction for ethylene-fueled supersonic combustion CFD

An Experimental Investigation on Forced Ignition Characteristics of Hydrocarbon Mixture Fuel in Scramjet Combustor

Combustion characteristics of a supersonic combustor model for a JAXA flight experiment

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