크리프-피로 하중조건하에서의 가스터빈 엔진 디스크의 균열성장 수명예측에 관한 연구

For gas turbine engines, safe life methodology has historically been used for fatigue life management of failure critical engine components. The objective of this study is to introduce the damage tolerant design concept instead of safe life methodology which has been used to apply the life management for aircraft engine component. Crack growth data were collected on a nickel base superalloy which have been subjected to combined static and cyclic loading at elevated temperatures. Stress analysis for turbine disk was carried out. The program for computing creep-fatigue crack growth was developed. We tried to estimate remaining life of turbine disk component under various temperature and conditions using creep-fatigue crack growth data. The largest stress was occurred in disk bore part. The magnitude and direction of the maximum stress were 937㎫ and in the hoop direction. Creep crack growth life in disk bore occupied approximately the half of the total crack growth life.