镍基单晶冷却叶片高温持久性的理论与试验研究  

Theory and experiment study on stress rupture properties of nickel-based single crystal cooling blades

作　　者：孙伟康[1] 徐元铭[1] 胡春燕[2] 刘曼卿[1] 刘新灵[2] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中航工业北京航空材料研究院,北京100095

出　　处：《固体火箭技术》2017年第4期488-492,500,共6页Journal of Solid Rocket Technology

基　　金：航空科学基金(KZ43150734);中航工业航材院创新基金(KJSJ140739);航空基金(2014ZE21009)

摘　　要：采用含有0~4排气膜孔的薄壁平板试样模拟镍基单晶冷却叶片,研究了气膜孔排布对镍基单晶冷却叶片高温持久性的影响,并基于晶体塑性理论建立单晶材料蠕变数值计算模型,将其编入Abaqus用户子程序中,对不同气膜孔排布的薄壁平板试件进行有限元分析。试验结果表明,在气膜孔数相同的情况下,随着气膜孔排数的逐渐增多,冷却叶片高温持久寿命不断降低,且下降趋势逐渐加剧。文中提出了基于有限元数据的高温持久寿命预测幂函数模型,在对应孔排布、应力、温度条件下,其相对误差均小于3%,有限元分析得到的应力场分布结果与试样的断口形貌相吻合。Thin-walled plate specimens with 0- 4 rows of film cooling holes were used to simulate the air-cooled turbine blades. The effect of holes distribution on the lifetime until the stress rupture of nickel-based single crystal cooling blades was studied.Based on the crystal plasticity theory, a creep numerical model for single crystal materials was established, which was implemented into the Abaqus user subroutine. Finite element analysis （ FEA ） was carried out for specimens with different distribution forms of cooling holes.Experimental results show that with the same number of holes on DD6 specimens,the more rows of the holes are, the shorter stress rupture lifetime specimens it has.Moreover,with the increase of rows number,the descending of creep properties gradually ac- celerates.Power function models based on FEA data were developed to predict the creep life of the samples with a certain amount of cooling holes under predetermined temperature and loading conditions.The fractional errors of the results are all within 3%.Stress distribution results obtained by FEA coincide with the fracture position and the shape of samples after experiments.

关 键 词：气膜孔分布 镍基单晶冷却叶片 DD6 薄壁平板试样 持久寿命 

分 类 号：V252[一般工业技术—材料科学与工程]