• 제목/요약/키워드: LMP(Larson-Miler Parameter)

검색결과 2건 처리시간 0.017초

핵융합로용 저방사화 철강재료(RAFs)의 크리프 특성평가 (Evaluation on Creep Properties of Reduced Activation Ferritic Steel(RAFs) for Nuclear Fusion Reactor)

  • 공유식;윤한기;남승훈
    • 한국해양공학회지
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    • 제18권2호
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    • pp.58-63
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    • 2004
  • Reduced Activation Ferritic/Martensitic Steels (RAFs) are leading candidntes for structural materials of a D-T fusion reactor. One of the RAFs, JLF-l (9Cr-2W-V, Ta) has been developed and has shown to have good resistance against high-fluency neutrino irradiation and good phase stability. Recently, in order to clarify the strengthening mechanisms at high temperatures, a new scheme to improve high temperature mechanical properties is desired. Therefore, the test technique development of high temperature creep behaviors for this material is very important. In this paper, the creep properties and creep life prediction, using the Larson-Miler parameter method for JLF-l to be used for fusion reactor materials or other high temperature components, are presented at the elevated temperatures of 50$0^{\circ}C$, 55$0^{\circ}C$, $600^{\circ}C$, $650^{\circ}C$ and 704$^{\circ}C$. It was confirmed, experimentally and quantitatively, that a creep life predictive equation, at such various high temperatures, is well derived mr the LMP method.

초내열합금 U720의 노출시험에 따른 크리프 특성 (Creep Properties of Superalloy Udimet 720 in relation to Exposed)

  • 공유식;오세규
    • 동력기계공학회지
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    • 제5권2호
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    • pp.57-62
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    • 2001
  • Gas turbine performance is highly dependent on the engine performance which is closely related to the engine materials since they are exposed to severe working environments, i.e, high temperature and high stresses. For this reason, advanced materials with improved properties are required for the engine. The purpose of this research is to develop key materials technologies for aircraft industry and to tester domestic production of related parts. In this paper, the real-time prediction of high temperature creep strength and creep life for nickel-based superalloy Udimet 720(high-temperature and high-pressure the gas turbine engine materials) was performed on round-bar type specimens under pure load at the temperatures of 538, 649 and $704^{\circ}C$.

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