Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector

High vapor pressure propellants such as nitrous oxide are widely used in experimental hybrid and liquid rockets as they can be used in a self-pressurization mode, eliminating the need for external pressurization or pumps and simplifying the design of the rocket system. This approach causes the two-p...

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Autores principales:	Tomasz Palacz, Jacek Cieślik
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	nitrous oxide mass flow rate self-pressurization injector two-phase flow Motor vehicles. Aeronautics. Astronautics TL1-4050
Acceso en línea:	https://doaj.org/article/9874cc05e0e6409bafc95d6a2106cf9d
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id	oai:doaj.org-article:9874cc05e0e6409bafc95d6a2106cf9d
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spelling	oai:doaj.org-article:9874cc05e0e6409bafc95d6a2106cf9d2021-11-25T15:57:09ZExperimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector10.3390/aerospace81103172226-4310https://doaj.org/article/9874cc05e0e6409bafc95d6a2106cf9d2021-10-01T00:00:00Zhttps://www.mdpi.com/2226-4310/8/11/317https://doaj.org/toc/2226-4310High vapor pressure propellants such as nitrous oxide are widely used in experimental hybrid and liquid rockets as they can be used in a self-pressurization mode, eliminating the need for external pressurization or pumps and simplifying the design of the rocket system. This approach causes the two-phase flow in the feed system and the injector orifices, which cannot be easily modeled and accounted for in the design. A dedicated test stand has been developed to better understand how the two-phase flow of the self-pressurizing propellant impacts the mass flow characteristics, enabling the simulation of the operating conditions in the rocket engine. The injectors have been studied in the range of <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mo>Δ</mo><mi mathvariant="normal">P</mi></mrow></semantics></math></inline-formula>. The flow regimes have been identified, which can be predicted by the SPI and HEM models. It has been shown that the two-phase flow quality upstream of the injector may impact the discharge coefficient in the SPI region and the accuracy of the HEM model. It has been found that the transition to the critical flow region depends on the L/D ratio of the injector orifice. A series of conclusions can be drawn from this work to design the rocket injector with a self-pressurizing propellant to better predict the mass flow rate and ensure stable combustion.Tomasz PalaczJacek CieślikMDPI AGarticlenitrous oxidemass flow rateself-pressurizationinjectortwo-phase flowMotor vehicles. Aeronautics. AstronauticsTL1-4050ENAerospace, Vol 8, Iss 317, p 317 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	nitrous oxide mass flow rate self-pressurization injector two-phase flow Motor vehicles. Aeronautics. Astronautics TL1-4050
spellingShingle	nitrous oxide mass flow rate self-pressurization injector two-phase flow Motor vehicles. Aeronautics. Astronautics TL1-4050 Tomasz Palacz Jacek Cieślik Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector
description	High vapor pressure propellants such as nitrous oxide are widely used in experimental hybrid and liquid rockets as they can be used in a self-pressurization mode, eliminating the need for external pressurization or pumps and simplifying the design of the rocket system. This approach causes the two-phase flow in the feed system and the injector orifices, which cannot be easily modeled and accounted for in the design. A dedicated test stand has been developed to better understand how the two-phase flow of the self-pressurizing propellant impacts the mass flow characteristics, enabling the simulation of the operating conditions in the rocket engine. The injectors have been studied in the range of <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mo>Δ</mo><mi mathvariant="normal">P</mi></mrow></semantics></math></inline-formula>. The flow regimes have been identified, which can be predicted by the SPI and HEM models. It has been shown that the two-phase flow quality upstream of the injector may impact the discharge coefficient in the SPI region and the accuracy of the HEM model. It has been found that the transition to the critical flow region depends on the L/D ratio of the injector orifice. A series of conclusions can be drawn from this work to design the rocket injector with a self-pressurizing propellant to better predict the mass flow rate and ensure stable combustion.
format	article
author	Tomasz Palacz Jacek Cieślik
author_facet	Tomasz Palacz Jacek Cieślik
author_sort	Tomasz Palacz
title	Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector
title_short	Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector
title_full	Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector
title_fullStr	Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector
title_full_unstemmed	Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector
title_sort	experimental study on the mass flow rate of the self-pressurizing propellants in the rocket injector
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/9874cc05e0e6409bafc95d6a2106cf9d
work_keys_str_mv	AT tomaszpalacz experimentalstudyonthemassflowrateoftheselfpressurizingpropellantsintherocketinjector AT jacekcieslik experimentalstudyonthemassflowrateoftheselfpressurizingpropellantsintherocketinjector
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Experimental Study on the Mass Flow Rate of the Self-Pressurizing Propellants in the Rocket Injector

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