Nozzle with spiral internal cooling channels
AssigneeAerojet-General Corporation
InventorRoss A. Hewitt
Life of this patent
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Abstract
A convergent-divergent rocket nozzle is formed by joining two coaxially aligned conical sections at a throat plane, each diverging outward from the throat plane. Coolant channels formed in the wall of the nozzle are arranged in spirals around the nozzle axis. Preferably, the conical sections are formed from platelet laminates rolled into conical form with a single spiral seam, and at least one of the conical sections is a composite of two or more component conical sections separately formed and then joined in a nested arrangement with the seams not superimposed. A further preferred construction is one in which the convergent end of one conical section is split radially into strips that are then spread apart to serve as bonding surfaces to bond to the other conical section.
Claims15
A convergent-divergent rocket nozzle comprising first and second conical sections coaxially aligned and joined at a throat plane with each of said conical sections diverging from said throat plane, said first conical section defining a longitudinal cone axis and comprising a wall with a plurality of internal coolant channels arranged in spirals around said cone axis.
Dependencies are inferred from the claim text.