Brennkammer eines Raketenantriebs

摘要

An improved engine construction, such as a rocket engine construction comprises a combustion chamber (12), a smooth wall nozzle (14), and a transition zone between the chamber and the smooth wall nozzle (14). The transition zone has a coolant system which includes a manifold (44) formed from a non-copper material through which a coolant flows. In a high heat transfer embodiment, the transition zone includes an additional manifold (40) formed from a copper based material. <IMAGE>