FIELD: engines and pumps.
SUBSTANCE: invention relates to rocket nozzle and method to control rocket engine exhaust gas flow. Rocket nozzle (8) represents dual-bell nozzle (10) and section (40A, 40B, 40C, 40D) designed to feed gas into chamber (80) formed by dual-bell nozzle. Gaseous combustion products flow in aforesaid chamber. Dual-bell nozzle comprises first stage bell-shaped nozzle (20) surrounding chamber upper section (81) and second stage bell-shaped nozzle (30) surrounding chamber lower section (82). Dual-bell nozzle has the point (12) of inflection between first stage and second stage nozzles. Gas feed section comprises gas inlet hole (45, 63) arranged on inner wall surface of the first stage nozzle. Gas is fed into aforesaid chamber via gas inlet hole.
EFFECT: higher efficiency.
18 cl, 13 dwg
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