Oxygen–methane rocket thrust chambers: Review of heat transfer experimental studies

TLDR

Oxygen–methane propulsion is viewed as a promising technology for future rockets, yet the high temperatures and heat fluxes inside thrust chambers limit component life and directly affect engine performance. The study surveys experimental literature on heat transfer in oxygen–methane thrust chambers to identify consolidated findings and remaining research gaps. Findings are grouped into hot‑gas heat transfer, coolant heat transfer and wall compatibility, and thrust‑chamber life.

Abstract

Nowadays oxygen–methane propulsion is considered of great potential for the next generation of operational rockets. In the development of a new liquid rocket engine with high-performance, an essential assessment is the thermal behavior of the thrust chamber. In fact, the flow of combustion gas inside the thrust chamber induces a level of wall temperature and heat flux such as to limit the life of this component. Furthermore, the heat transfer within the thrust chamber directly impacts the performance of the rocket engine. In the present study, a thorough survey of the open literature concerning the experimental activities focused on the heat transfer within oxygen–methane thrust chambers is carried out in order to identify the most consolidated results and the aspects that would require further investigations. The results are divided into three main categories: hot-gas side heat transfer; coolant heat transfer and wall compatibility; thrust chamber life.