CPC F02K 9/972 (2013.01) [B23P 15/008 (2013.01); F02K 9/52 (2013.01); F02K 9/62 (2013.01); F02K 9/64 (2013.01)] | 3 Claims |
1. A method for manufacture of a liquid rocket engine thruster body, the method comprising:
forming the thruster body to define a combustion chamber, a throat and a nozzle having a thrust axis, the thruster body having an interior surface and an exterior surface;
milling plural cooling channels in an outer surface of the thruster body exterior surface along the thrust axis, the plural cooling channels each having a depth from the outer surface defining a variable depth along the thrust axis in a circumferential orientation and in a predetermined pattern, at least some of the plural cooling channels having convergent bifurcation and divergent bifurcation to pass through a reduced circumference of the nozzle; and
covering the outer surface of the thruster body exterior surface to enclose the plural cooling channels,
wherein the predetermined pattern comprises a continuous sine wave form having an amplitude and wavelength proportional relative to an average of the variable depth.
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