摘要
对某涡桨发动机高压涡轮盘进行了有限元应力分析,结果表明:在各工作状态,涡轮盘的应力水平在各工作状态都处于弹性范围,最大应力点始终处于轮盘的偏心孔处;采用斯贝MK202发动机应力标准(EGD-3)提供的方法,对该涡轮盘的低循环疲劳寿命进行了估算。
FE stress analysis of a turboprop engine HP turbine disk is completed. The results show that the stress level of turbine disk is within the elastic range at various operation conditions and maximum stress location is still at the eccentric orifice. The LCF Ufe of the turbine disk is evaluated using the method provided by SPEY MK202 engine stress standard （ EGD - 3 ）.
出处
《航空发动机》
2006年第4期16-18,共3页
Aeroengine
