Design of a film cooled dual-bell nozzle

The design of a film cooled dual-bell nozzle is presented. The nozzle is part of a thrust chamber assembly that adopts an existing LOX/GH2 thrust chamber. The dual-bell base nozzle, including the gaseous hydrogen cooling film injection, is a downscaled redesign of an already tested film cooled TIC n...

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Veröffentlicht in:	Acta astronautica 2019-05, Vol.158, p.342-350
Hauptverfasser:	Stark, Ralf, Génin, Chloé, Mader, Christian, Maier, Dietmar, Schneider, Dirk, Wohlhüter, Michael
Format:	Artikel
Sprache:	eng
Schlagworte:	Additive layer manufacturing Cooling Design Design optimization Dual-bell nozzle Film cooling Hydrogen Injector head Liquid oxygen Mass flow Nozzles Numerical simulation Redesign Rocket engine Rockets Sea level Thrust chambers
Online-Zugang:	Volltext
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