Parametric study of thermal behavior of thrust chamber cooling channels

A numerical investigation is adopted for two dimensional thermal analysis of rocket thrust chamber wall (RL10), employing finite difference model with iterative scheme (implemented under relaxation factor of 0.9 for convergence) to compute temperature distribution within thrust chamber wall (which i...

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Autor principal:	Karima E. Amori
Formato:	article
Lenguaje:	EN
Publicado:	Al-Khwarizmi College of Engineering – University of Baghdad 2007
Materias:	Thrust chamber multi layer wall cooling duct CFD. Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
Acceso en línea:	https://doaj.org/article/0af8fb0dc55a4b7599e51c5b1617bf85
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spelling	oai:doaj.org-article:0af8fb0dc55a4b7599e51c5b1617bf852021-12-02T04:16:48ZParametric study of thermal behavior of thrust chamber cooling channels1818-1171https://doaj.org/article/0af8fb0dc55a4b7599e51c5b1617bf852007-01-01T00:00:00Zhttp://www.iasj.net/iasj?func=fulltext&aId=2389https://doaj.org/toc/1818-1171A numerical investigation is adopted for two dimensional thermal analysis of rocket thrust chamber wall (RL10), employing finite difference model with iterative scheme (implemented under relaxation factor of 0.9 for convergence) to compute temperature distribution within thrust chamber wall (which is composed of Nickel and Copper layers). The analysis is conducted for different boundary conditions: only convection boundary conditions then combined radiation, convection boundary conditions also for different aspect ratio (AR) of cooling channel. The results show that Utilizing cooling channels of high aspect ratio leads to decrease in temperature variation across thrust chamber wall, while no effects on heat transferred to the coolant is indicated. The radiation has a considerable effect on the computed wall temperature values. Karima E. AmoriAl-Khwarizmi College of Engineering – University of BaghdadarticleThrust chambermulti layer wallcooling ductCFD.Chemical engineeringTP155-156Engineering (General). Civil engineering (General)TA1-2040ENAl-Khawarizmi Engineering Journal, Vol 3, Iss 3, Pp 1-12 (2007)
institution	DOAJ
collection	DOAJ
language	EN
topic	Thrust chamber multi layer wall cooling duct CFD. Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
spellingShingle	Thrust chamber multi layer wall cooling duct CFD. Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040 Karima E. Amori Parametric study of thermal behavior of thrust chamber cooling channels
description	A numerical investigation is adopted for two dimensional thermal analysis of rocket thrust chamber wall (RL10), employing finite difference model with iterative scheme (implemented under relaxation factor of 0.9 for convergence) to compute temperature distribution within thrust chamber wall (which is composed of Nickel and Copper layers). The analysis is conducted for different boundary conditions: only convection boundary conditions then combined radiation, convection boundary conditions also for different aspect ratio (AR) of cooling channel. The results show that Utilizing cooling channels of high aspect ratio leads to decrease in temperature variation across thrust chamber wall, while no effects on heat transferred to the coolant is indicated. The radiation has a considerable effect on the computed wall temperature values.
format	article
author	Karima E. Amori
author_facet	Karima E. Amori
author_sort	Karima E. Amori
title	Parametric study of thermal behavior of thrust chamber cooling channels
title_short	Parametric study of thermal behavior of thrust chamber cooling channels
title_full	Parametric study of thermal behavior of thrust chamber cooling channels
title_fullStr	Parametric study of thermal behavior of thrust chamber cooling channels
title_full_unstemmed	Parametric study of thermal behavior of thrust chamber cooling channels
title_sort	parametric study of thermal behavior of thrust chamber cooling channels
publisher	Al-Khwarizmi College of Engineering – University of Baghdad
publishDate	2007
url	https://doaj.org/article/0af8fb0dc55a4b7599e51c5b1617bf85
work_keys_str_mv	AT karimaeamori parametricstudyofthermalbehaviorofthrustchambercoolingchannels
_version_	1718401350191022080

Parametric study of thermal behavior of thrust chamber cooling channels

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