It is a challenging task to investigate the regenerative cooling of the variable thrust
LOX/LCH4 expander cycle rocket engine. The decreasing methane mass flow rate leads to …

Facing the need to increase the accuracy of rocket engine design tools, the present work
introduces an innovative methodology for the design and optimization of rocket engine …

Hot-fire tests were performed with a single-injector research combustor featuring a large
optical access (255× 38 mm) for flame imaging. These tests were conducted with the …

In this study, the flow and heat transfer of supercritical hydrogen flowing inside a rocket
engine cooling channel with arc ribs and variable heat flux is presented using numerical …

In the realm of reusable rocket technology, the methane–oxygen propellant combination has
gained prevalence in recent years. However, understanding of design parameters affecting …

Hot fire tests were performed using a single-injector research combustor featuring a large
optical access window (255× 38 mm) for flame visualisation. Three test campaigns were …

The rapid development of space launch vehicle has put forward increasingly strict
requirements for engine startup characteristics and thrust regulation capabilities. The flow …

This paper investigates different types of longitudinal mode coupling in subscale rocket
combustion chambers using experimental data and numerical simulations. Based on a one …

Adequate understanding of the combustion and heat transfer characteristics are considered
key points for the development of methane engines. In this paper, a methane combustion …

Hot fire tests were performed with a single-injector research combustor featuring a large
optical access window (255x38 mm) for flame visualisation. Three test campaigns were …