FIELD: engines and pumps.
SUBSTANCE: invention relates to solid-propellant rocket engines, in particular, to joints between the combustion chamber rear wall and the nozzle. The joint between the rocket engine combustion chamber rear wall (14) and nozzle (20) incorporates means (50) of a mechanical joint coupling the nozzle with the rear wall, at least, axially, heat barrier (40) and, at least, one sealing part (32, 34) arranged in mating section (30) limited by opposed adjoining surfaces of the rear wall and nozzle. Heat barrier (40) includes, at least, one heat-resistant fibre material forming cord (42) wound, in the said mating section, around the chamber lengthwise axis (A), the cord, or cords, being designed to provide for continuity of heat barrier (40) along the circumference.
EFFECT: better combustion gas cooling ensured by high-efficiency heat barrier.
17 cl, 12 dwg
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