叶根前缘倒角对低压涡轮转子叶片强度的影响

Influence of the Blade Root Front Edge Chamfering on the Low Pressure Turbine Blade Strength

针对某型航空发动机低压涡轮转子叶片在叶根前缘倒角处发生应力集中的问题,研究了叶根前缘倒角半径对低压涡轮转子叶片强度的影响。研究结果表明,随着叶根前缘倒角半径的增加,低压涡轮转子叶片根部前缘倒角处应力集中效应降低,可作为减少低压涡轮转子叶片疲劳破坏和断裂失效的措施。叶片表面气动力载荷、离心力载荷是导致低压涡轮转子叶片根部前缘倒角处应力集中的主要原因。其中,气动力载荷引起的应力占总等效应力的78%,离心力载荷引起的应力占总等效应力的22%,温度场载荷引起的应力可忽略。

For the problem of stress concentration of aircraf t engine LPT blade root front edge chamfering,This paper research on influence of the blade root front edge chamfering on the L PT blade strength and analysis of causes.Results show that,wit h the increase of blade root front edge chamfer radius,the stress concentration effect of the leading edge chamfer of LPT bladeo ort is reduced,which can be used as a measure to reduce fatiguei lfuare and fracture failure.The aerodynamic load and centrifugal force load on the blade are the main causes of the stress concentroant iat the blade root front edge chamfering.The equivalent stress csaeud by the aerodynamic load accounts for the Seventy-eight percentgae of the total equivalent stress;The equivalent stress caused b y centrifugal force load accounts for the Twenty-two percentage of the total equivalent stress;The equivalent stress caused by the temperature field load can be ignored.