Patent Number: 6,308,408

Title: Fabrication process for combustion chamber/nozzle assembly

Abstract: 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.

Inventors: Myers; W. Neill (Huntsville, AL), Cornelius; Charles S. (Huntsville, AL)

Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

International Classification: F02K 9/00 (20060101); F02K 9/97 (20060101); F02K 9/62 (20060101); B23P 015/00 ()

Expiration Date: 10/30/2018