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从DZ125定向凝固空心涡轮叶片割取小尺寸试样,并进行两种温度(980℃和1050℃)下单轴拉伸试验以及980℃、219 MPa下的蠕变持久试验。作为对比,同时从DZ125板材上割取小尺寸试样并进行试验。结果表明,相比于标准试件,从叶片上取得的试件的拉伸极限强度明显降低,持久寿命时间也大为缩短;与板材试件相比,从叶片上取得的试件拉伸极限强度和持久寿命也较低,表明涡轮叶片存在局部力学性能弱化。采用标准试件试验数据设计定向凝固涡轮叶片并不能准确表征叶片局部力学性能。小试样试验可作为研究涡轮叶片不同部位力学性能差异的可行方法。
Small size specimens were cut from DZ125 directional solidified turbine blades and tested under both uniaxial tension (980 ° C and 1050 ° C) and creep endurance at 980 ° C and 219 MPa. In comparison, small size specimens were cut from the DZ125 sheet and tested. The results show that compared with the standard specimen, the ultimate tensile strength of the specimen obtained from the blade is significantly reduced, and the life time of the specimen is greatly shortened. Compared with the plate specimen, the tensile limit of the specimen obtained from the blade The strength and long-term life are also lower, indicating weakening of the local mechanical properties of turbine blades. The use of standard specimen test data to design the directional solidification turbine blade does not accurately characterize the local mechanical properties of the blade. Small sample test can be used as a feasible method to study the difference of mechanical properties of different parts of turbine blades.