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为了验证某型航空发动机粉末合金涡轮盘低循环疲劳寿命,在旋转试验器上进行了涡轮转子的低循环疲劳寿命试验。在试验过程中有轮缘凸块和配重块断裂飞出,导致试验失败,得出该低循环疲劳试验故障的主要原因是裂纹起始部位的局部应力偏高。通过建立故障部位的单圆弧、双圆弧和3圆弧局部模型进行有限元计算,研究了转接圆角处的应力与转接圆角半径的关系。研究结果表明:采用3圆弧转接方法对粉末合金涡轮盘寿命考核部位进行改进设计是最佳方案,降低了轮盘考核部位应力,提高了轮盘寿命,并通过了试验验证。
In order to verify the low cycle fatigue life of an aero-engine powdered alloy turbine disk, a low cycle fatigue life test of the turbine rotor was performed on a spin tester. In the course of the test, the flange bump and the counterweight broke out and broke the test, which led to the failure of the low cycle fatigue test. The main reason for the failure was that the local stress at the crack initiation site was high. The finite element method is used to establish the single-arc, double-arc and three-arc local model of the fault location, and the relationship between the stress at the fillet fillet and the fillet radius is studied. The results show that the optimal design of the life assessment site of the powder alloy turbine disk is the best solution by adopting the 3 arc transition method, which reduces the stress of the disk inspection site and improves the life of the disk, and has passed the test verification.