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在日本设计研制的原型LE-7助推火箭发动机中,已研制了四种制造推力室的方法:CIP(冷等静压制)成形法、镍电铸法、扩散焊接法和铜粉钎焊法。本报告的目的是要从推力室壁的最大弹性应力观点出发比较和评估这些方法。所分析的冷却槽式推力室是根据LE-7发动机的设计任务书设计的。在下面的分析中把推力室壁的压力和热载荷作为边界条件。作为第一步,为了简化起见,用轴对称薄壳模型进行分析,以评价整个燃烧室的应力场。然后用二维弹性分析法计算具有最大应力的喉部壁板。这些分析证明,四种加工方法中CIP成形法具有最低的应力场。进一步分析表明,CIP法还可以在CIP成形的外筒与外壳之间嵌入绝热层加以改进,这样,就能降低燃烧室壁的最大应力。
Among the prototype LE-7 booster rocket engines designed and engineered in Japan, four methods for manufacturing thrust chambers have been developed: CIP (cold isostatic pressing) forming, nickel electroforming, diffusion welding and copper powder brazing . The purpose of this report is to compare and evaluate these methods from the point of view of the maximum elastic stress of the thrust chamber wall. The analysis of the cooling groove thrust chamber is based on LE-7 engine design task book design. In the following analysis, the thrust chamber wall pressure and thermal load are used as the boundary conditions. As a first step, for simplicity, an axisymmetric shell model was used to analyze the stress field throughout the combustion chamber. Then calculate the throat wall with the maximum stress by two-dimensional elasticity analysis. These analyzes demonstrate that CIP forming has the lowest stress field among the four processing methods. Further analysis shows that the CIP method can also be improved by embedding a thermal insulation layer between the CIP-formed outer cylinder and the housing so that the maximum stress on the combustion chamber wall can be reduced.