摘要
航空发动机涡轮盘属于限寿件,为了保证结构完整性,适航审定时需要对涡轮盘进行损伤容限评估。针对涡轮盘损伤容限适航要求对FAA发布的咨询通告AC33.70-2进行技术解析,研究航空发动机涡轮盘孔部位的损伤容限评估流程。结合该流程,对某型发动机高压1级涡轮盘的简化模型的偏心孔部位进行损伤容限评估,验证了该方法的可用性,为涡轮盘适航审定技术的研究提供支持。
Turbine disks of aero-engines are life-limited parts,and damage tolerance assessment is requested during certification to ensure the structural integrity. For the airworthiness requirements for damage tolerance of turbine disks,the Advisory Circular AC33.70-2 issued by FAA is analyzed technically,and damage tolerance assessment procedure of hole features in aero-engine turbine disks is studied. On the basis of this procedure,a damage tolerance assessment is conducted on a simplified model of the 1st stage high pressure turbine disk with hole feature of a certain type of engine,and availability of this method is verified. Some support for the research on the technology of turbine disk＇s certification is provided.
出处
《装备制造技术》
2016年第5期105-109,共5页
Equipment Manufacturing Technology
基金
民航科技创新引导资金(编号:MHRD20130221)
关键词
航空发动机
涡轮盘
适航审定
损伤容限
aero-engine
life-limited parts
airworthiness certification
damage tolerance
