High performance rocket engine having a stepped expansion combustion chamber and method of making the same

摘要: An improved rocket engine combustion chamber including a first having diameter and located intermediate to propellant injector second that is larger than the diameter. The extends radially outward from suddenly at intersection between chambers. Film cooling provided by providing stratified layer of low temperature fluid adjacent inner wall surrounding primary core high gases. sudden stepped expansion interface chambers provides secondary recirculation mixing propellants facilitates complete combustion. In an additional aspect, surface may be made material has degree thermal conductivity minimize gradients.