Nozzle with spiral internal cooling channels
AssigneeAerojet-General Corporation
InventorRoss A. Hewitt
Life of this patent
Estimating the term…
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.
Claims14
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, and said first conical section comprising a laminate of platelets formed from a laminate sheet closed into conical form along a single seam arranged in a spiral around said axis.
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, said first and second conical sections each having convergent ends and divergent ends and each having a cone angle;
- at least one of said first and second conical sections terminating at its convergent end in a segment that is split longitudinally into at least six strips that are spread apart at angles equal to the cone angle of the other of said first and second conical sections;
- said strips bonded to said other conical section.
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,
- said first and second conical sections each having convergent ends and divergent ends and a cone angle;
- said first conical section terminating at its convergent end in a segment that is split longitudinally into at least six strips that are spread apart at angles equal to the cone angle of the said second conical section and are bonded to said second conical section;
- and
- said second conical section terminating at its convergent end in a segment that is split longitudinally into at least six strips that are spread apart at angles equal to the cone angle of the said first conical section and are bonded to said first conical section.
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, said first conical section having a divergent end opposite said throat plane, and said first conical section terminating at said divergent end in a segment that is split longitudinally into a plurality of strips that are bent outward to form an expanded rim.
Dependencies are inferred from the claim text.