Life Evaluation of Gas Turbine Engine Disk based on Retirement for Cause Concept

Retirement For Cause 개념에 의한 가스터빈 디스크 수명의 평가

  • 남승훈 (한국표준과학연구원 산업측정표준부) ;
  • 박종화 (경상대학교 수송기계공학부) ;
  • 김종엽 (삼성테크윈 파워시스템연구소)
  • Published : 2002.02.01


For gas turbine engines, the safe life methodology has historically been used fur fatigue life management of failure critical engine components. The safe retirement limit is necessarily determined by a conservative life evaluation procedure, thereby many components which have a long residual life are discarded. The objective of this study is to introduce the damage tolerant design concept into the life management for aircraft engine component instead of conservative fatigue life methodology which has been used for both design and maintenance. 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 fur turbine disk was carried out. The program for computing creep-fatigue crack growth was developed. The residual lifes of turbine disk component under various temperatures and conditions using creep-fatigue crack growth data were estimated. As the result of analysis, it was confirmed that retirement fur cause concept was applicable to the evaluation of residual life of retired turbine disk which had been designed based on the conventional fatigue life methodology.


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