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METHOD OF PRODUCING LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER NOZZLE WITH INNER AND OUTER SHELLS

机译:具有内,外壳的液体火箭发动机燃烧室喷嘴的生产方法

摘要

FIELD: process engineering.;SUBSTANCE: invention may be used in production of liquid-propellant rocket engine combustion chamber nozzles. Channels of cooling circuit are milled on nozzle inner shell surface. In milling said channels on moving off cooling circuit working section, depth of channels is reduced to produce wedge-like slots making ''traps'' to pull in excess solder alloy in nozzle shell rough tolerance. Total volume of said channels in rough tolerance exceeds that of possible excess solder alloy. Shells are assembled on side of nozzle smaller diameter to produce rough tolerance. Solder alloy is located to carry out soldering in vacuum-compression furnace to cut rough tolerance off.;EFFECT: ruled out seals in cooling circuit channels.;2 dwg
机译:技术领域:本发明可用于生产液体推进剂火箭发动机燃烧室喷嘴。冷却回路的通道在喷嘴内壳表面上铣削。在离开冷却回路工作段的过程中铣削所述通道时,通道的深度会减小,以产生楔形的槽,从而形成“陷阱”,以将多余的焊料合金拉入喷嘴外壳的粗公差范围内。以粗略公差表示的所述通道的总体积超过可能过量的焊料合金的总体积。壳体组装在喷嘴直径较小的一侧,以产生较大的公差。放置焊料合金以便在真空压缩炉中进行焊接以减少粗略的公差。效果:排除了冷却回路通道中的密封。2 dwg

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