Wall Heat Loads in a Cryogenic Rocket Thrust Chamber During Thermoacoustic Instabilities

A subscale, research rocket thrust chamber operating with cryogenic oxygen and hydrogen exhibits self-excited transverse-mode instabilities with amplitudes of more than 80% of the steady combustion chamber pressure (peak-to-peak) for some operating conditions. During unstable combustion, an increase...

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Veröffentlicht in:	Journal of propulsion and power 2021-11, Vol.37 (6), p.952-962
Hauptverfasser:	Govaert, Thomas, Armbruster, Wolfgang, Hardi, Justin S, Suslov, Dmitry, Oschwald, Michael, Zandbergen, Barry T. C
Format:	Artikel
Sprache:	eng
Schlagworte:	Amplitudes Combustion chambers Heat flux Heat transfer Rocket engines Rocket thrust Rockets Structural damage Thermal analysis Thrust chambers
Online-Zugang:	Volltext
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