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Transpiration cooling experiments in free-piston shock tunnel HIEST

Tanno, H. und Komuro, T. und Itoh, K. und Kuhn, Markus und Petkov, Ivaylo und Esser, Burkard (2016) Transpiration cooling experiments in free-piston shock tunnel HIEST. 8th European Workshop on Thermal Protection Systems and Hot Structures, 19.-22. April 2016, Noordwijk, Niederlande.

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Offizielle URL: http://congrexprojects.com/custom/16c07/

Kurzfassung

Transpiration cooling technique is one of the most promising candidates as the next‐generation TPS ‐thermal protection system for reentry or planetary entry vehicles. Although many researchers have produced numerous works over these decades to use the technique to cool spacecraft or aircraft components, which are exposed to high heat‐load, such as rocket engines or gas‐turbine blades. Nevertheless, most of the studies were focusing on the applications in a turbulent boundary layer. On the other hand, planetary entry or reentry vehicles have to fly from hypersonic to subsonic speed. Since flight altitude is also changed from the space to the ground, Reynolds number will change from fully‐laminar to fully‐turbulent condition. Moreover, the extremely high flightspeed will produce thermochemical non‐equilibrium flow in the boundary layer. For the application of the cooling technique on reentry vehicle design, it is crucial to address the knowledge about the characteristic of transpiration effects on boundary layer under such the extreme high‐stagnation flow condition. Recent studies were all carried in low‐density flow, or in perfect gas flow (low enthalpy flow), under which flow condition does not agree to real flight condition. The free‐piston shock tunnel HIEST, which can produce high‐enthalpy and high‐density namely high‐Reynolds number test free‐steam suitable for the study of transpiration cooling. The aim of the present research is to obtain transpiration cooling characteristics with a generic flat plate in HIEST under high stagnation enthalpy and pressure condition, which stagnation enthalpy was 4 to 20MJ/kg and stagnation pressure was 12MPa to 60MPa. The transpiration cooling on the flat plate surface was conducted with Helium or Nitrogen gas injection through a porous material located downstream of the leading edge, which material had already used for previous Hypersonic studies. Heat flux distribution on the flat plate was measured along the centerline. The small amount of gas‐injection reduces surface heat flux. Even so, heat flux augmentation was observed with large amount of gas‐injection due to the onset of early transition of the boundary layer.

elib-URL des Eintrags:https://elib.dlr.de/105525/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Transpiration cooling experiments in free-piston shock tunnel HIEST
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Tanno, H.JAXANICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Komuro, T.JAXANICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Itoh, K.JAXANICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Kuhn, MarkusMarkus.Kuhn (at) dlr.dehttps://orcid.org/0000-0002-0633-2327NICHT SPEZIFIZIERT
Petkov, IvayloIvaylo.Petkov (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Esser, BurkardBurkard.Esser (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:Juli 2016
Referierte Publikation:Nein
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Status:veröffentlicht
Stichwörter:Transpiration cooling, Atmospheric entry, High enthalpy testing, Non-Equilibrium flow, Porous media, Shock tunnel
Veranstaltungstitel:8th European Workshop on Thermal Protection Systems and Hot Structures
Veranstaltungsort:Noordwijk, Niederlande
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:19.-22. April 2016
Veranstalter :ESA/ESTEC
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 - Raumfahrzeugsysteme - Rückkehrtechnologie (alt)
Standort: Köln-Porz , Stuttgart
Institute & Einrichtungen:Institut für Bauweisen und Strukturtechnologie > Raumfahrt - System - Integration
Institut für Aerodynamik und Strömungstechnik > Über- und Hyperschalltechnologien
Hinterlegt von: Esser, Dr.-Ing. Burkard
Hinterlegt am:05 Sep 2016 09:10
Letzte Änderung:29 Mär 2023 00:28

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