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Manufacturing method of regenerative cooling combustion chamber for rocket and regenerative cooling combustion chamber for rocket

机译:火箭蓄冷燃烧室的制造方法和火箭蓄冷燃烧室

摘要

PROBLEM TO BE SOLVED: To provide a process of manufacture of a regenerative cooling combustion chamber for rocket capable of manufacturing the regenerative cooling combustion chamber for rocket in a short time and at a low cost and to provide the regenerative cooling combustion chamber for rocket.SOLUTION: This invention comprises: a groove machining step of forming a groove 14a opened at an outer peripheral surface 11a in an inner cylinder 11 constituting a combustion chamber 1 provided with several flow passages 14 for flowing cooling fluid; a core charging step of charging heat melted wax W in the groove 14a; electroforming step of forming a plating layer 12 by applying electroforming to the outer peripheral surface 11a of the inner cylinder 11; an outer cylinder forming step of forming an outer cylinder 13 by applying laser powder padding process to a surface 12a of the plating layer 12, and serving as a flow passage forming step of melting wax W with laser heat and discharging it to form flow passages 14; and a heat treatment step of applying heat treatment against the inner cylinder 11, the plating layer 12 and the outer cylinder 13 to increase their strengths.SELECTED DRAWING: Figure 7
机译:要解决的问题:提供一种用于火箭的蓄冷冷却燃烧室的制造方法,该工艺能够在短时间内以低成本制造用于火箭的蓄冷冷却燃烧室,并提供用于火箭的蓄冷冷却燃烧室。本发明包括:槽加工步骤,该槽加工步骤是在构成燃烧室1的内缸11中的外周表面11a上形成开口的槽14a,该燃烧室1设置有用于使冷却液流动的多个流路14。芯填充步骤是在槽14a中填充热融蜡W。通过对内筒11的外周面11a进行电铸而形成镀层12的电铸工序。外筒形成步骤,该外筒形成步骤是通过对镀层12的表面12a进行激光粉末填充处理而形成外筒13的步骤,并且用作通过激光加热使蜡W熔化并排出以形成流道14的流道形成步骤。 ;以及对内筒体11,镀层12和外筒体13进行热处理以提高其强度的热处理步骤。图7

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