A rocket engine chamber (10) has a back structure (20) and a heat exchanger structure (18) located radially inwardly of the back structure (20). The heat exchanger structure (18) has a plurality of integrally formed cooling passageways with adjacent ones o...

A system for cooling a combustion chamber (32) of an engine, such as a rocket engine, is provided. The system (32) has a plurality of coolant tubes or passages (34) surrounding the combustion chamber (32), a torroidal coolant-collection manifold (36) for r...

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 ...

A method for forming a coolant system for a rocket engine combustion chamber is provided. The method comprises the steps of providing a plurality of tubes 22 formed and shaped into the profile of a nozzle with each of the tubes having a constantly expandin...

The combustion chamber has a cooling unit and an inner combustion chamber wall. The wall has recesses, which are formed so that a stable border layer of the gas flow, which is formed near the inner wall when the combustion chamber is operational, is destab...