摘要
根据航空发动机压气机在实际工作中已用时间不同的两组叶片的恒幅振动疲劳试验数据 ,通过统计分析确定其疲劳破坏前应力循环次数的分布。根据 Miner疲劳损伤累积理论 ,找出叶片在实验中与在实际工作中所受疲劳损伤的当量关系 ,从而确定新叶片在实际工作中疲劳寿命的分布 ,并计算出新叶片在一定可靠度下的疲劳寿命。
On the basis of the results of fatigue test of two groups of vanes from vane compressor of aerial-engines which have different length of service life and statistical analysis ,we got the times-chart of stress cycle which occurs before the damage.Then on the basis of Miner's theory of fatigue damage accumulation,we obtained the equivalent relation between the fatigue damage from the test and that from actual situation.Therefor,we got the chart of fatigue service life in actual situation of new vanes.And then,we have calculated the fatigue of new vanes service life under a certain reliability.
