Christoph Bauer  , Reinhold Baumann , Guido Kurth , Ralf Schlaps , Johan Steelant  and Philipp Störchle

DoI Number XXX-YYY-ZZZ

Conference Number HiSST 2018-1161

SABRE – Synergetic Air Breathing Rocket Engine – combines the advantages of a high specific impulse air breathing engine with a high thrust/weight ratio rocket motor. During air breathing mode, SABRE – operating in a combined turbomachinery based cycle of the core engine and ramjet cycle of the bypass burner – captures the ambient air as oxidizer [1]. To minimize drag, the adjustable air intake system is capable of aligning the shock structure to the free stream Mach number and capturing the maximum possible air mass flow.

The system is designed in such a way that the core engine is operating under nearly constant conditions – air mass flow, temperature and static pressure – independent from Mach number and altitude. In consequence, a significant percentage of the air mass flow has to be bypassed at low altitudes. This air can be used to generate additional thrust with the excess hydrogen of the core engine cycle in a ring of single ramjet modules [2]. Independent from the air mass flow through the bypass burner, the system should hold the static pressure of the pre-compressed air at the pre-cooler inlet within a predefined, quite narrow band. In conclusion, the bypass burner system should control the static pressure at the pre-cooler inlet as well as the air mass flow to the core engine while maximizing the thrust. This paper summarizes the evolution of a design concept for the ramjet bypass burner system.

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In Categories: HiSST 2018, Hypersonic Flight Dynamics, Hypersonic Propulsion, Propulsion Systems and Components, Supersonic and Hypersonic Aircraft Design, Testing and Evaluation
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