【摘要】 航空发动机与燃气轮机作为国之重器，对保障国防安全和能源安全具有重要意义。随着发动机效率的不断提升，涡轮进气口温度不断提高。先进叶片往往采用高代次单晶高温合金材料制备，具有薄壁、多孔复杂冷却结构，且表面涂覆先进涂层，因而先进单晶叶片结构越来越精细复杂，服役过程中叶片不同部位温度场、应力场分布变化更大，其损伤机制无法通过传统棒状试样的变形损伤机制完全体现。基于先进单晶叶片的结构特点及服役环境特点，综述了叶片结构(薄壁、气膜孔)、二次枝晶取向(二次取向)及先进涂层等单一因素及多因素耦合作用对单晶合金拉伸、蠕变及疲劳等典型性能的影响规律及损伤机理研究，并对镍基单晶高温合金近服役环境性能研究的发展方向进行展望。更多还原

【Abstract】 Aero-engines and gas turbines are of great significance for ensuring national defense security and national energy security. With the improvement of engine efficiency, the turbine inlet temperature increases continuously. High-generation single crystal superalloys have been used for manufacturing of advanced blades. The blades always possess complex cooling structures with thin wall and cooling holes, and usually possess advanced coatings. Therefore, the temperature gradient and stress gradient in the different parts of the blades would be higher. The damage mechanisms of the traditional rod samples may not fully represent the failure of the blades. Based on the complex structure and severe service environment, the effects of single factor or coupled factors, such as structure(thin-wall, film cooling holes), secondary dendrite orientation(secondary orientation), and advanced coatings on the typical properties of single crystal superalloys were reviewed in the present paper. Further, the invastigation directions of the performance of nickel-based single crystal superalloys in the typical service environments were prospected.更多还原