Patent ID: 6079101
Filing Date: 2000-06-27
Classification: B23P,F02K,F05D,F23M,F23R,Y10T

Abstract:
A method of fabricating a rocket engine, comprising the steps offabricating a combustion chamber comprising an annular wall with a chamber wall inner surface and a chamber wall outer surface, the annular wall includinga first axial region having a first inner diameter of the chamber wall inner surface,a second axial region having a second inner diameter of the chamber wall inner surface, wherein the second inner diameter is greater than the first inner diameter, andan inner wall step transition between the first axial region and the second axial region, the step of fabricating including the steps ofproviding a combustion chamber wall blank that is oversize relative to the final combustion chamber wall, andremoving material from the combustion chamber wall blank to reach the final annular wall by a removal method which does not substantially deform and cold work any material which is not removed from the wall blank;providing an injector; andattaching the combustion chamber and the injector, the step of attaching including the steps ofbonding an annular metallic deposit to the first axial region of the combustion chamber,providing an annular adaptor ring,first welding the adaptor ring to the metallic deposit, andsecond welding the adaptor ring to the injector.