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Analytical Study of Stationary Temperature Field in Transpiration Cooled Porous Wall

Zhukov, V. und 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.

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Kurzfassung

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.

Dokumentart:Zeitschriftenbeitrag
Titel:Analytical Study of Stationary Temperature Field in Transpiration Cooled Porous Wall
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Zhukov, V.Viktor.Zhukov@dlr.de
Haidn, O.TU München; Fakultät für Maschinenwesen
Datum:28 Mai 2012
Erschienen in:Journal of Aerospace Engineering
Referierte Publikation:Ja
In Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Ja
DOI :10.1177/0954410012446899
ISSN:0893-1321
Status:veröffentlicht
Stichwörter:transpiration cooling, injector head, heat transfer, porous media
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Raumtransport
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):R - Antriebsystemtechnik - Raketenantriebtests
Standort: Lampoldshausen
Institute & Einrichtungen:Institut für Raumfahrtantriebe > Raketenantriebe
Hinterlegt von: Michaela Hanke
Hinterlegt am:28 Nov 2012 11:29
Letzte Änderung:07 Feb 2013 20:27

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