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Shape Optimization and Reliability Analysis of the Dovetail of the Disk of a Gas Turbine Engine

가스터빈엔진 디스크의 도브테일 형상 최적화와 신뢰도 해석

  • Huh, Jae-Sung (Aero-propulsion Division, Korea Aerospace Research Institute)
  • 허재성 (한국항공우주연구원 항공엔진실)
  • Received : 2013.11.07
  • Accepted : 2014.02.02
  • Published : 2014.04.01

Abstract

The most critical rotating parts of a gas turbine engine are turbine blades and disc, given that they must operate under severe conditions such as high turbine inlet temperature, high speeds, and high compression ratios. Owing to theses operating conditions and high rotational speed energy, some failures caused by turbine disks and blades are categorized into catastrophic and critical, respectively. To maximize the margin of structural integrity, we aim to optimize the vulnerable area of disc-blade interface region. Then, to check the robustness of the obtained optimized solution, we evaluated structural reliability under uncertainties such as dimensional tolerance and fatigue life variant. The results highlighted the necessity for and limitations of optimization which is one of deterministic methods, and pointed out the requirement for introducing reliability-based design optimization which is one of stochastic methods. Thermal-structural coupled-filed analysis and contact analysis are performed for them.

Keywords

Shape Optimization;Reliability Analysis;Low Cycle Fatigue;Gas Turbine engine;Turbine Disk;Dovetail

Acknowledgement

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

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