Investigation on the Stress Variation of Turbine Blade by Minute Blade Angle Adjustment

摘要

Nowadays aircraft engine is increasingly requested for higher performance, higher speed, higher temperature, lighter weight, higher reliability and longer life. To successfully achieve these objectives the turbine engine designer must face the problem of preventing turbine blade fatigue failure due to the high stress in its root area. With the aid of finite element analysis, the main purpose of this paper is to reduce the stress of blade root, without degrading the engine performance, by adjusting the blade angle in order to take advantage of centrifugal force of blade slant to counterbalance the relevant aerodynamic force, and lengthen blade fatigue life.