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随着火箭发动机结构重量的减轻,对关键部位的法兰盘厚度要求愈来愈薄,传统的密封方法己经不能满足要求。缠绕垫圈是一种较好的密封形式。它成型简单方便,对密封面要求不高、密封效果良好、价格低廉,有较高的实用价值。本试验是通过测量材料的室温与高温弹性性能和缠绕密封垫圈的高温压缩回弹性能试验,选出适于在不同温度下使用的缠绕垫圈的骨架材料。并研究了不同热处理状态对GH169合金弹性模量的影响,选择出最佳热处理方案。该密封垫圈经发动机热试车,取得了满意的结果。
With the reduction of the weight of the rocket engine structure, the requirements for the flange thickness of the key parts are getting thinner and thinner. The traditional sealing method can no longer meet the requirements. Wound gasket is a better form of sealing. It is simple and convenient molding, less demanding on the sealing surface, good sealing effect, low price and high practical value. This test is through the measurement of materials at room temperature and high temperature elastic properties and high temperature compression wound gasket compression resilience test, selected suitable for use at different temperatures spiral wound gasket material. The effects of different heat treatment conditions on the elastic modulus of GH169 alloy were studied, and the best heat treatment scheme was selected. The ferrule heat test by the engine, and achieved satisfactory results.