tuyeres System-rocket engine

The nozzle system for a rocket engine comprises a set of individual nozzles (1) distributed in a ring around a central core (2) is axially symmetrical shape having a central axis (z). Each individual nozzle (1) placed at the periphery of the central core (2) comprises a neck (12) of circular section receiving gases from a combustion chamber (11) and a diverging portion (13) tangent to the central core ( 2). The diverging portion (13) has an outlet section (14) having first and second lateral sides (14c, 14d) that converge radially towards the central axis (z) of the central core (2), an outer side (14b) curve having its convexity facing outwards and an inner side (14a) situated in the vicinity of the central core (2). The inner side (14a) has a smaller dimension than the chord defined from the outer curved side (14b).