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为了获得综合性能良好的航空发动机高压压气转子叶片用TC4棒材,采用相变点以上大变形和相变点以下多火次小变形两种变形方式相结合的工艺路线,制备航空发动机转子叶片用TC4Φ20 mm、Φ40 mm棒材,通过力学数据、金相组织及超声波探伤检验的试验手段进行分析研究,结果表明:(1)按照试验路线生产的TC4棒材,低倍组织均为模糊晶,不存在裂纹、折叠、气孔、金属或非金属夹杂、偏析、缩尾和其它肉眼可见的缺陷;高倍组织分布均匀,晶粒尺寸细小,没有流线形成,均为等轴双态组织;(2)按照试验路线生产的TC4棒材,室温力学性能、高温力学性能等综合性能良好,均满足标准要求,且性能稳定;(3)按照试验路线生产的TC4棒材,超声波探伤检验满足Φ0.8~12 d B杂波水平要求,无缺陷波。
In order to obtain TC4 bar for high-pressure aerodynamic rotor blades with good overall performance, aero-engine rotor blades were prepared by a combination of two deformation modes, namely, a large deformation above the transformation point and a small deformation below the transformation point TC4Φ20 mm and Φ40 mm bars were analyzed by means of mechanical data, microstructure and ultrasonic flaw detection. The results showed that: (1) TC4 bar and low magnification produced according to the test route were all fuzzy crystals, There are cracks, folds, pores, metal or non-metallic inclusions, segregation, tailing and other macroscopic defects; high magnification distribution, small grain size, no streamline formation, According to the test line production TC4 bar, room temperature mechanical properties, high temperature mechanical properties such as good overall performance, meet the standards, and stable performance; (3) According to the test line production TC4 bar, ultrasonic testing to meet the inspection Φ0.8 ~ 12 d B Clutter level requirements, no defect wave.