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AssigneeThe United States of America as represented by the Administrator of the National Aeronautics and Space Administration
InventorsW. Neill Myers, Charles S. Cornelius
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An integral, lightweight combustion chamber/nozzle assembly for a rocket engine has a refractory metal shell defining a chamber of generally frusto-conical contour. The shell communicates at its smaller end with a rocket body, and terminates at its larger end in a generally contact contour, which is open at its terminus and which serves as a nozzle for the rocket engine. The entire inner surface of the refractory metal shell has a thermal and oxidation barrier layer applied thereto. An ablative silica phenolic insert is bonded to the exposed surface of the thermal and oxidation barrier layer. The ablative phenolic insert provides a chosen inner contour for the combustion chamber and has a taper toward the open terminus of the nozzle. A process for fabricating the integral, lightweight combustion chamber/nozzle assembly is simple and efficient, and results in economy in respect of both resources and time.
A process for fabricating an integral, lightweight combustion chamber/nozzle assembly wherein said assembly comprises (1) 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 smaller end with a rocket body, and terminating at its larger end in a generally conical contour which is open at the terminus thereof and which serves as a nozzle for the rocket engine;
A process for fabricating an integral, lightweight combustion chamber/nozzle assembly wherein said assembly comprises (1) a shell of 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 larder 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 servers as a nozzle for the rocket engine;
Dependencies are inferred from the claim text.