Liquid or gas bipropellant injecting device for rocket engine, has annular channels oriented in converging manner by forming predefined angles to create liquid bipropellant bodies, where bodies create impact between them

摘要

The device has concentric annular running channels (41, 42) respectively connected to tori (61, 62) and projecting though respective annular injection sections (31, 32). The annular channels are oriented in a converging manner by forming predefined angles (alpha1, alpha2) to create liquid bipropellant bodies in output. The liquid bipropellant bodies create an impact between them according to a spray crown or bipropellant mixture at a predetermined distance from an upstream end (91) and near an axis of a combustion chamber (9). The upstream end forms a base of the chamber.