Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector

The rocket ejector refers to a core component of a rocket-based combined cycle (RBCC) engine. The ignition is of critical significance for rocket ejection. Reliable and stable ignition crucially determines the normal operation of the engine. In this paper, a thrust chamber with coaxial swirl injecto...

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Autores principales:	Bingyang Liu, Ping Jin, Yixin Ma, Yaqun Qi, Guobiao Cai, Yuanjun Zhang
Formato:	article
Lenguaje:	EN
Publicado:	Hindawi Limited 2021
Materias:	Motor vehicles. Aeronautics. Astronautics TL1-4050
Acceso en línea:	https://doaj.org/article/b1f3209b286e46309b1492519a916a67
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spelling	oai:doaj.org-article:b1f3209b286e46309b1492519a916a672021-11-22T01:11:16ZExperimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector1687-597410.1155/2021/7002104https://doaj.org/article/b1f3209b286e46309b1492519a916a672021-01-01T00:00:00Zhttp://dx.doi.org/10.1155/2021/7002104https://doaj.org/toc/1687-5974The rocket ejector refers to a core component of a rocket-based combined cycle (RBCC) engine. The ignition is of critical significance for rocket ejection. Reliable and stable ignition crucially determines the normal operation of the engine. In this paper, a thrust chamber with coaxial swirl injector for the RBCC rocket ejection was developed and tested. Gas oxygen (GOX) and kerosene acted as propellants. As revealed from the test results, the process of ignition pressurizing comprised four phases. The oxygen prefilling time before ignition slightly impacted the ignition time, whereas it affected the peak pressure of ignition. In a confined range, the peak pressure decreased as the prefilling time was extended. The ignition was simulated by building a numerical model, and the results well complied with the experimentally achieved results. The numerical model is capable of specifically indicating the position of the kernel of fire and the process of flame propagation. The simulation results reveal that the propellant could form a combustible condition within 4 ms. The kernel was 6 mm away from the injector, located at the oxygen and kerosene mixing interface and approaching the upper wall. The above results reflected the vital role of the central recirculation zone formed by the prefilled oxygen. The ignition energy was transported near the injector under the convection effect, which ignited the stoichiometric mixture, and the entire ignition could reach a stable state within 20 ms. The numerical model which was developed in this paper can help clarify the combustion mechanism.Bingyang LiuPing JinYixin MaYaqun QiGuobiao CaiYuanjun ZhangHindawi LimitedarticleMotor vehicles. Aeronautics. AstronauticsTL1-4050ENInternational Journal of Aerospace Engineering, Vol 2021 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	Motor vehicles. Aeronautics. Astronautics TL1-4050
spellingShingle	Motor vehicles. Aeronautics. Astronautics TL1-4050 Bingyang Liu Ping Jin Yixin Ma Yaqun Qi Guobiao Cai Yuanjun Zhang Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector
description	The rocket ejector refers to a core component of a rocket-based combined cycle (RBCC) engine. The ignition is of critical significance for rocket ejection. Reliable and stable ignition crucially determines the normal operation of the engine. In this paper, a thrust chamber with coaxial swirl injector for the RBCC rocket ejection was developed and tested. Gas oxygen (GOX) and kerosene acted as propellants. As revealed from the test results, the process of ignition pressurizing comprised four phases. The oxygen prefilling time before ignition slightly impacted the ignition time, whereas it affected the peak pressure of ignition. In a confined range, the peak pressure decreased as the prefilling time was extended. The ignition was simulated by building a numerical model, and the results well complied with the experimentally achieved results. The numerical model is capable of specifically indicating the position of the kernel of fire and the process of flame propagation. The simulation results reveal that the propellant could form a combustible condition within 4 ms. The kernel was 6 mm away from the injector, located at the oxygen and kerosene mixing interface and approaching the upper wall. The above results reflected the vital role of the central recirculation zone formed by the prefilled oxygen. The ignition energy was transported near the injector under the convection effect, which ignited the stoichiometric mixture, and the entire ignition could reach a stable state within 20 ms. The numerical model which was developed in this paper can help clarify the combustion mechanism.
format	article
author	Bingyang Liu Ping Jin Yixin Ma Yaqun Qi Guobiao Cai Yuanjun Zhang
author_facet	Bingyang Liu Ping Jin Yixin Ma Yaqun Qi Guobiao Cai Yuanjun Zhang
author_sort	Bingyang Liu
title	Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector
title_short	Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector
title_full	Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector
title_fullStr	Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector
title_full_unstemmed	Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector
title_sort	experimental and numerical investigations on the ignition of rbcc gas-oxygen/kerosene rocket ejector
publisher	Hindawi Limited
publishDate	2021
url	https://doaj.org/article/b1f3209b286e46309b1492519a916a67
work_keys_str_mv	AT bingyangliu experimentalandnumericalinvestigationsontheignitionofrbccgasoxygenkerosenerocketejector AT pingjin experimentalandnumericalinvestigationsontheignitionofrbccgasoxygenkerosenerocketejector AT yixinma experimentalandnumericalinvestigationsontheignitionofrbccgasoxygenkerosenerocketejector AT yaqunqi experimentalandnumericalinvestigationsontheignitionofrbccgasoxygenkerosenerocketejector AT guobiaocai experimentalandnumericalinvestigationsontheignitionofrbccgasoxygenkerosenerocketejector AT yuanjunzhang experimentalandnumericalinvestigationsontheignitionofrbccgasoxygenkerosenerocketejector
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Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector

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