Abstract: A thrust chamber liner includes a metallic combustion chamber having an annular protrusion extending radially away from an exterior surface of the combustion chamber adjacent to its injector opening. A metallic nozzle is coupled to the combustion chamber at its throat opening. A composite material encases the exterior surface of the combustion chamber, but is only bonded to the annular protrusion.

Abstract: A thrust chamber liner for a rocket engine includes a main combustion chamber (MCC) and a nozzle. A composite wrap covers the outside surface of the MCC and the outside surface of the nozzle.

Abstract: A thrust chamber liner includes a main combustion chamber (MCC) with MCC coolant channels extending axially there along. Each MCC coolant channel has a port at an outside surface of the MCC. A nozzle is integrated with the MCC. The nozzle has nozzle coolant channels extending axially there along. A coolant-supply manifold, integrated with one of the MCC and the MCC and nozzle, is in fluid communication with each port in the MCC coolant channels.

Abstract: A method for fabricating a thrust chamber liner for a rocket engine commences with a ring made from a first material on a build plate. A base layer of a second material in powder form is deposited on the exposed axial end of the ring. A laser beam is directed towards the base layer and the ring such that energy associated with the laser beam melts the base layer and a portion of the ring adjacent to the base layer. A melted portion of the base layer intermixes with a melted portion of the ring. Following this step, additional layers of the second material are deposited on the base layer. The first axial end of the ring is then exposed and additional layers of the first material are deposited on the first axial end of the ring.