A Study on Variations of the Low Cycle Fatigue Life of a High Pressure Turbine Nozzle Caused by Inlet Temperature Profiles and Installation Conditions

고압터빈 노즐에서 입구온도분포와 장착조건에 따른 저주기 피로 수명 영향에 대한 연구

  • Huh, Jae Sung (Aero-propulsion Research Office, Korea Aerospace Research Institute) ;
  • Kang, Young Seok (Aero-propulsion Research Office, Korea Aerospace Research Institute) ;
  • Rhee, Dong Ho (Aero-propulsion Research Office, Korea Aerospace Research Institute) ;
  • Seo, Do Young (School of Mechanical and Aerospace Engineering, Pusan Nat’l Univ.)
  • 허재성 (한국항공우주연구원 항공엔진연구단) ;
  • 강영석 (한국항공우주연구원 항공엔진연구단) ;
  • 이동호 (한국항공우주연구원 항공엔진연구단) ;
  • 서도영 (부산대학교 항공우주공학과)
  • Received : 2015.05.14
  • Accepted : 2015.09.05
  • Published : 2015.11.01


High pressure components of a gas turbine engine must operate for a long life under severe conditions in order to maximize the performance and minimize the maintenance cost. Enhanced cooling design, thermal barrier coating techniques, and nickel-base superalloys have been applied for overcoming them and furthermore, material modeling, finite element analysis, statistical techniques, and etc. in design stage have been utilized widely. This article aims to evaluate the effects on the low cycle fatigue life of the high pressure turbine nozzle caused by different turbine inlet temperature profiles and installation conditions and to investigate the most favorable operating condition to the turbine nozzle. To achieve it, the structural analysis, which utilized the results of conjugate heat transfer analysis as loading boundary conditions, was performed and its results were the input for the assessment of low cycle fatigue life at several critical zones.


High Pressure Turbine Nozzle;Directionally Solidified Material;Turbine Inlet Temperature Profile;Installation Condition;Low Cycle Fatigue Life;Critical Plane Approach


Grant : 중소형 항공기용 터보팬 엔진의 고압터빈 냉각 설계기술 개발 및 시험평가 기술 구축


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