ROCKET ENGINE LAVAL NOZZLE WITH GAS INJECTION DEVICE

摘要

A rocket engine Laval nozzle comprises a nozzle throat, a first expansion section (1), connected to the throat, and a second expansion section (2) joined to the first expansion section. The expansion sections (1,2) define an inner nozzle surface that' delimits an expansion zone for producing thrust in direction of the nozzle axis by expansion of an exhaust gas flow discharged through the throat. A ring slot (3), formed at the junction of the first and second expansion sections, extends circumferentially around the nozzle axis. Gas discharge ducts (5) of a gas injection device are connected to the ring slot for injection of additional gas into the expansion zone. A wall (12), which extends in the ring slot between the first and second expansion sections, comprises through holes (7) disposed about the nozzle axis. These holes (7) allow fluid communication between the expansion zone and the outside of the nozzle.