Modeling of a Reduced Hybrid H2–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion

A hybrid H2–air kinetic scheme of 11 species and 15 reactions is developed, which is capable of simulating the high-temperature air reaction flows and H2–O2 combustion flows respectively or simultaneously. Based on the Gupta scheme...

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Autores principales:	Longfei Li, Jiangfeng Wang
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	hypersonic reactive flow H<sub>2</sub>–O<sub>2</sub> combustion reactions sensitivity analysis ignition delay time shock-induced detonation kinetic scheme Technology T
Acceso en línea:	https://doaj.org/article/923a55e5bac544e7904af57a28023546
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spelling	oai:doaj.org-article:923a55e5bac544e7904af57a280235462021-11-25T17:28:17ZModeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion10.3390/en142277281996-1073https://doaj.org/article/923a55e5bac544e7904af57a280235462021-11-01T00:00:00Zhttps://www.mdpi.com/1996-1073/14/22/7728https://doaj.org/toc/1996-1073A hybrid H<sub>2</sub>–air kinetic scheme of 11 species and 15 reactions is developed, which is capable of simulating the high-temperature air reaction flows and H<sub>2</sub>–O<sub>2</sub> combustion flows respectively or simultaneously. Based on the Gupta scheme, the mole fraction varying with a Mach number at specific conditions is analyzed, and the weakly-ionized 7-species 7-reaction scheme is selected. The effect of nitrogenous species on the H<sub>2</sub>–O<sub>2</sub> combustion is analyzed by a zero-dimensional simulation of steady-state and unsteady-state combustion under specified conditions, and the selected dominant nitrogenous reaction N + OH = NO + H is distinguished by the production rate of the nitrogenous species. The thermodynamic properties are verified by comparison using the NIST–JANAF database. The reaction rate coefficients of the dominant reaction of the hybrid kinetic scheme distinguished by a sensitivity analysis are corrected. The proposed kinetic scheme is validated by a zero-dimensional calculation of the ignition delay time and two-dimensional computational fluid dynamics (CFD) simulation with finite-rate chemistry on the shock-induced sub-detonative and super-detonative combustion. The ignition delay time of the hybrid kinetic scheme is almost in the middle between the Shang scheme and Jachimowski scheme, and all the calculated ignition delay times are acceptably greater than the experiments due to the errors of the experiments and numerical models. The clearly captured bow shock wave and combustion front using the hybrid kinetic scheme and Shang scheme are almost the same, which is strongly consistent with the schlieren image. In addition, a good agreement of the flow characteristics and mass fraction of the species along the stagnation line is also obtained, which indicates the accuracy and reasonableness of the hybrid kinetic scheme to simulate hybrid H<sub>2</sub>–air reactive flows.Longfei LiJiangfeng WangMDPI AGarticlehypersonic reactive flowH<sub>2</sub>–O<sub>2</sub> combustion reactionssensitivity analysisignition delay timeshock-induced detonationkinetic schemeTechnologyTENEnergies, Vol 14, Iss 7728, p 7728 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	hypersonic reactive flow H<sub>2</sub>–O<sub>2</sub> combustion reactions sensitivity analysis ignition delay time shock-induced detonation kinetic scheme Technology T
spellingShingle	hypersonic reactive flow H<sub>2</sub>–O<sub>2</sub> combustion reactions sensitivity analysis ignition delay time shock-induced detonation kinetic scheme Technology T Longfei Li Jiangfeng Wang Modeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion
description	A hybrid H<sub>2</sub>–air kinetic scheme of 11 species and 15 reactions is developed, which is capable of simulating the high-temperature air reaction flows and H<sub>2</sub>–O<sub>2</sub> combustion flows respectively or simultaneously. Based on the Gupta scheme, the mole fraction varying with a Mach number at specific conditions is analyzed, and the weakly-ionized 7-species 7-reaction scheme is selected. The effect of nitrogenous species on the H<sub>2</sub>–O<sub>2</sub> combustion is analyzed by a zero-dimensional simulation of steady-state and unsteady-state combustion under specified conditions, and the selected dominant nitrogenous reaction N + OH = NO + H is distinguished by the production rate of the nitrogenous species. The thermodynamic properties are verified by comparison using the NIST–JANAF database. The reaction rate coefficients of the dominant reaction of the hybrid kinetic scheme distinguished by a sensitivity analysis are corrected. The proposed kinetic scheme is validated by a zero-dimensional calculation of the ignition delay time and two-dimensional computational fluid dynamics (CFD) simulation with finite-rate chemistry on the shock-induced sub-detonative and super-detonative combustion. The ignition delay time of the hybrid kinetic scheme is almost in the middle between the Shang scheme and Jachimowski scheme, and all the calculated ignition delay times are acceptably greater than the experiments due to the errors of the experiments and numerical models. The clearly captured bow shock wave and combustion front using the hybrid kinetic scheme and Shang scheme are almost the same, which is strongly consistent with the schlieren image. In addition, a good agreement of the flow characteristics and mass fraction of the species along the stagnation line is also obtained, which indicates the accuracy and reasonableness of the hybrid kinetic scheme to simulate hybrid H<sub>2</sub>–air reactive flows.
format	article
author	Longfei Li Jiangfeng Wang
author_facet	Longfei Li Jiangfeng Wang
author_sort	Longfei Li
title	Modeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion
title_short	Modeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion
title_full	Modeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion
title_fullStr	Modeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion
title_full_unstemmed	Modeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion
title_sort	modeling of a reduced hybrid h<sub>2</sub>–air kinetic scheme integrating the effect of hypersonic reactive air with supersonic combustion
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/923a55e5bac544e7904af57a28023546
work_keys_str_mv	AT longfeili modelingofareducedhybridhsub2subairkineticschemeintegratingtheeffectofhypersonicreactiveairwithsupersoniccombustion AT jiangfengwang modelingofareducedhybridhsub2subairkineticschemeintegratingtheeffectofhypersonicreactiveairwithsupersoniccombustion
_version_	1718412298447486976

Modeling of a Reduced Hybrid H<sub>2</sub>–Air Kinetic Scheme Integrating the Effect of Hypersonic Reactive Air with Supersonic Combustion

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