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Analytical Study of Stationary Temperature Field in Transpiration Cooled Porous Wall

Zhukov, V. and Haidn, O. (2012) Analytical Study of Stationary Temperature Field in Transpiration Cooled Porous Wall. Journal of Aerospace Engineering. DOI: 10.1177/0954410012446899. ISSN 0893-1321.

Full text not available from this repository.

Abstract

A one-dimensional heat conduction problem in a porous wall with a cooling fluid was considered theoretically. The case related to the porous injector head of rocket engine, where the heat flux is directed toward a coolant flow, was studied. The equations for the temperatures of permeable media and coolant were solved analytically. Using reasonable assumptions the equation system was simplified and the order of equations as reduced. The margins, where the used assumptions are valid, were defined. The solution is expressed in hyperbolic functions and shows that the flow of coolant leads to the increase in the temperature gradient near the hot side of porous wall. The expressions for the temperatures of wall and coolant at hot-gas-side wall are given. The thickness of wall, at which the temperature of the hot wall is independent on the wall thickness, was found.

Document Type:Article
Title:Analytical Study of Stationary Temperature Field in Transpiration Cooled Porous Wall
Authors:
AuthorsInstitution or Email of Authors
Zhukov, V.Viktor.Zhukov@dlr.de
Haidn, O.TU München; Fakultät für Maschinenwesen
Date:28 May 2012
Journal or Publication Title:Journal of Aerospace Engineering
Refereed publication:Yes
In Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
DOI:10.1177/0954410012446899
ISSN:0893-1321
Status:Published
Keywords:transpiration cooling, injector head, heat transfer, porous media
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Antriebsystemtechnik - Raketenantriebtests
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Raketenantriebe
Deposited By: Michaela Hanke
Deposited On:28 Nov 2012 11:29
Last Modified:07 Feb 2013 20:27

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