Combustion chamber for a liquid fuel rocket motor has a porous section at the chamber wall with structured permeability towards the front plate for a transpirant cooling action

摘要

The combustion chamber, for a liquid fuel rocket propellant motor, has at least one transpiration cooling (9), an injector head (1) with a front plate (2) and coaxial injectors (3), and an insert (4) with a coaxial shrouding sleeve (5). The inner wall of the combustion chamber has a porous section (9) at a gap from the front plate (2) of 15-20 times the inner dia. of the shrouding sleeve (5). The zone of the porous section (9) towards the front plate (2) has a permeability which is 1.1-2.5 times greater than in the zone away from the front plate (2). The porous section (9) has recesses at the zone towards the front plate (2), where the side coolant feed (10) is located, and the recesses in the porous section give it a wall thickness of 0.3-0.4 times the thickness of the porous section (9) where there are no recesses.