Patent ID: 6164060
Filing Date: 2000-12-26
Classification: F02K,Y10T

Abstract:
An integral, lightweight combustion chamber/nozzle assembly for a rocket engine, which assembly comprises:a shell of a refractory metal having a configuration defining a chamber of generally frusto-conical contour, the refractory metal shell having an inner and an outer surface and communicating at its base or larger end with a rocket body, and terminating at its smaller end in a tube of generally cylindrical contour which is open at the terminus thereof and which serves as a nozzle for the rocket engine;the entire inner surface of the refractory metal shell having applied thereto a thermal and oxidation barrier layer; andan ablative silica phenolic insert bonded to the exposed surface of the thermal and oxidation barrier layer and configured to provide an inner contour for the combustion chamber, the ablative silica phenolic insert having a taper or gradual reduction in thickness thereof toward the open terminus of the nozzle.