THERMAL SCIENCE

International Scientific Journal

Authors of this Paper

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Zhongwen Li

,

Jingbo Wang

,

Xiangyuan Li

COMBUSTION SIMULATIONS OF SCRAMJET COMBUSTOR USING REDUCED MECHANISM OF SURROGATE FUEL FOR REGENERATIVE COOLING PYROLYSIS PRODUCTS

ABSTRACT
Taking the surrogate fuel (64% ethylene and 36% methane in mole percentage) for regenerative cooling pyrolysis products used in HIFiRE-2 scramjet combustor as an example, present work systematically explores the workflow of the integrated mechanism reduction for surrogate fuel of pyrolysis products, the kinetic performance verification of the preferred reduced mechanism, and the combustion simulation application of the reduced mechanism in scramjet combustor. A static integrated reduction strategy is performed to obtain reduced mechanism for the surrogate fuel with the NUIGMech1.2 as detailed mechanism under wide conditions for temperature range of 900-1800 K, pressure range of 1-4 atmosphere, and equivalence ratio range of 0.25-5.0. A reduced mechanism (34 species and 181 reactions) with remarkably reduced size is obtained, which presents favorable performance in comprehensive kinetic validations. With this compact and high-fidelity reduced mechanism, the combustion simulations for the scramjet combustor are carried out combining with tabulation of dynamic adaptive chemistry for run-time speed-up. The simulation results of static pressure profiles obtained for cold and hot states match well with the experimental measurements for the two conditions with flight Mach number of 5.84 and 6.50. Meanwhile, the flow and combustion characteristics of the two conditions are investigated based on simulation results. The integrated reduction strategy and systematic kinetic verification used in pre-sent work provide reference values for the application of more complex surrogate fuel mechanisms in scramjet combustor combustion simulation.
KEYWORDS
Pyrolysis products, Surrogate fuel, Integrated reduction strategy, Reduced mechanism, scramjet combustor, Combustion simulation
PAPER SUBMITTED: 2023-12-23
PAPER REVISED: 2024-03-20
PAPER ACCEPTED: 2024-03-23
PUBLISHED ONLINE: 2024-05-18
DOI REFERENCE: https://doi.org/10.2298/TSCI231223114L
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2024, VOLUME 28, ISSUE Issue 5, PAGES [4041 - 4065]
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Combustion simulations of scramjet combustor using reduced mechanism of surrogate fuel for regenerative cooling pyrolysis products

© 2024 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, National Institute of the Republic of Serbia, Belgrade, Serbia. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial-NoDerivs 4.0 International licence