Abstract: A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.

Abstract: A channel cutting tool may include an arbor that connects to a rotating spindle of a machining tool or a similar spinning part of a machining tool. Two slot cutting blades may be fixedly mounted to the arbor. An inner washer may be fixedly mounted on the arbor between the cutting blades and establish the blade spacing. An outer washer may be rotationally mounted to the inner washer with a smaller thickness to facilitate rotation relative to the two cutting blades. The arbor rotates about a longitudinal rotation axis, which may also the rotation axis for the cutting blades, the inner washer, and the outer washer. The outer washer functions as a depth-limiting safeguard for the channel cutting tool.