Mixing and Combustion in Supercritical O2/CH4 Liquid Rocket Injectors

Ierardo, Nicola; Congiunti, Alessandro; Bruno, Claudio

doi:10.2514/6.2004-1163

Cited by 11 publications

(1 citation statement)

References 13 publications

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“…In fact, there are several well-known reasons, still pushing research and economic efforts into developing and consolidating methanefuelled space propulsion systems [1][2][3][4]. Although specific impulse is generally lower than hydrogen-based systems, methane exhibits some advantages such as storability, relative ease of handling, and soft cryogenic skills, due to the higher density and critical temperature values, respectively; if compared to rocket-grade kerosene, methane results are cleaner since it does not produce residues (e.g., coking) during the combustion, and this represents also a key factor for developing reusable rockets [5][6][7][8][9][10]. Given these reasons, the worldfamous company SpaceX chose methane-based technology, concentrating investments on Raptor's reusable engines [11].…”

Section: Introductionmentioning

confidence: 99%

Transcritical Behavior of Methane in the Cooling Jacket of a Liquid-Oxygen/Liquid-Methane Rocket-Engine Demonstrator

2022

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The successful design of a liquid rocket engine is strictly linked to the development of efficient cooling systems, able to dissipate huge thermal loads coming from the combustion in the thrust chamber. Generally, cooling architectures are based on regenerative strategies, adopting fuels as coolants; and on cooling jackets, including several narrow axial channels allocated around the thrust chambers. Moreover, since cryogenic fuels are used, as in the case of oxygen/methane-based liquid rocket engines, the refrigerant is injected in liquid phase at supercritical pressure conditions and heated by the thermal load coming from the combustion chamber, which tends to experience transcritical conditions until behaving as a supercritical vapor before exiting the cooling jacket. The comprehension of fluid behavior inside the cooling jackets of liquid-oxygen/methane rocket engines as a function of different operative conditions represents not only a current topic but a critical issue for the development of future propulsion systems. Hence, the current manuscript discusses the results concerning the cooling jacket equipping the liquid-oxygen/liquid-methane demonstrator, designed and manufactured within the scope of HYPROB-NEW Italian Project. In particular, numerical results considering the nominal operating conditions and the influence of variables, such as the inlet temperature and pressure values of refrigerant as well as mass-flow rate, are shown to discuss the fluid transcritical behavior inside the cooling channels and give indications on the numerical methodologies, supporting the design of liquid-oxygen/liquid-methane rocket-engine cooling systems. Validation has been accomplished by means of experimental results obtained through a specific test article, provided with a cooling channel, characterized by dimensions representative of HYPROB DEMO-0A regenerative combustion chamber.

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