某型发动机150h持久试车涡轮部件寿命消耗研究

Research on Life Consumption of Turbine Components for an Aeroengine in 150 Hours Endurance Test

基于某型航空发动机的技术特征,应用有限元素法分析了该型发动机涡轮部件的模拟稳态温度场和应力场,确定了叶片和轮盘的寿命分析考核点。利用采集到的473组飞行任务参数记录和150h持久试车数据,基于EGD-3疲劳分析理论和Miner线性累积损伤理论计算了叶片和轮盘各考核点的低循环疲劳损伤。采用插值法和拉森-米勒公式,分别计算了叶片和轮盘的持久损伤,并利用时间-循环分数相加法进行了疲劳/持久损伤分析,得到了叶片和轮盘各考核点的总损伤。按照等效损伤原则,完成了该型发动机150h持久试车寿命消耗向外场飞行使用寿命消耗的等当量换算。

Based on the technology characteristics of an aeroengine, the simulative steady temperature field and stress field of the 2nd HP turbine rotor blade and disk were analyzed by finite element method. The life access points of blade and disk were conformed. Based on the fatigue analysis theory of EGD-3 and damage cumulative theory of Miner, the fatigue damage of access points were evaluated by using real flight parameters in 473 flight missions and firing test data in 150 hours factory endurance test. The endurance damage of blade and disk were achieved by the method of interpolation and Larson-Miller formula. Meanwhile, fatigue and endurance united damage were analyzed by means of time-cycle fraction add method, and the total damage of blade and disk access points were gained. The aeroengine life consumption equivalent transformation from 150 hours factory endurance test to outfield flight is conducted under the principle of equivalent damage.