Patent ID: 6829884
Filing Date: 2004-12-14
Classification: B23P,F02K,F05D,Y10T

Abstract:
A method of fabricating a rocket engine combustion chamber, comprising the steps of:a) forming a coolant liner having an outside surface; b) forming a plurality of coolant channels on the outside surface of the coolant liner; c) forming at least two inner conformal throat support sections and at least two outer conformal throat support sections; d) assembling said at least two inner conformal throat support sections around said outside surface of said coolant liner to form a closed inner conformal throat outside surface, said inner conformal throat support sections being joined at inner throat seam lines; e) assembling said at least two outer conformal throat support sections around said closed inner conformal throat outside surface so as to cover said inner throat seam lines, to form a liner throat support assembly; f) assembling an inlet manifold and an outlet manifold around said liner throat support assembly to form a hot isostatic press (HIP) assembly; and, g) HIP'ing said HIP assembly to form a HIP'ed assembly, wherein fabrication costs are minimized by obviating any requirement of a structural jacket during HIP'ing and weight is minimized as a result of utilizing said inner and outer conformal throat supports.