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석창성(Chang-sung Seok),최정훈(Jung-Hoon Choi),김형익(Hyung-Ick Kim),김종학(Jong-Hak Kim),유승훈(Seung-Hun Yu) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.11
It has been known that engineering plastics including ABS and HIPS resin for Air-conditioner's blade are very sensitive to the temperature changes. Therefore, in this paper we investigated the effect of temperature by tensile test and the degradation of air-conditioner's blade by the twisting fracture test.
오스테나이트계 Fe-Ni based 합금강의 열화 시간에 의한 탄화물 거동과 기계적 물성 변화에 대한 연구
김기근(Keekeun Kim),박수(Soo Park),석창성(Chang-Sung Seok),최재구(Jae Gu Choi),김가연(Gayeon Kim) 대한기계학회 2018 大韓機械學會論文集A Vol.42 No.11
Fe-Ni-Cr 오스테나이트계 합금강 중 NCF3015 소재는 Ni 원소의 함량을 증가시켜 고온 기계적 물성을 우수하게 만든 소재이다. 고온 기계적 물성은 미세조직의 형상과 밀접한 관계가 있으며 미세조직의 형상은 고온노출 온도와 시간에 따라 변할 수 있기 때문에, 재료의 고온 미세조직 변화와 기계적 물성변화에 대한 연구가 필요하다. 본 연구에서는 950℃에서 NCF3015 소재의 열화 시간에 따른 미세조직 및 탄화물 변화와 기계적 물성과의 관계를 분석하기 위해 Thermo-calc 프로그램을 통한 평형 상태도 해석으로 NCF3015 소재의 고온 미세조직 변화를 예측하였으며, 실험적으로 열화된 시편의 미세조직 분석을 통해 해석결과와 비교하였다. 또한 인장시험과 비커스 경도를 측정함으로써 열화 시간에 따른 기계적 물성변화를 분석하였으며 이를 탄화물 거동변화와 관련 지어 두 변화의 상관관계를 도출하였다. NCF3015 is a Fe-Ni-Cr austenitic alloy steel that increases the content of Ni elements and which results in excellent high-temperature mechanical properties. High-temperature mechanical properties are closely related to the microstructure, and the shape of the microstructure can be changed by the exposure temperature and time. Therefore, it is necessary to study the changes in the high-temperature microstructure and mechanical properties of materials. In this research, to analyze the relationship between microstructural and carbide changes, as well as the mechanical properties of NCF3015 at 950℃, an equilibrium-state analysis is performed using the Thermo-calc program to determine the microstructural changes. The results are compared with the experimental results obtained. In addition, the tensile test and the Vicker"s hardness test are conducted to determine the variation in the mechanical properties with degradation time, which was correlated with the changes of microstructural and carbide behavior.
SA508 CL.1a 탄소강 배관소재의 파괴저항특성 평가
석창성,강병구,Seok, Chang-Sung,Kang, Byoung-Gu 대한기계학회 1999 大韓機械學會論文集A Vol.23 No.7
The objective of this paper is to evaluate the fracture resistance characteristics of SA508 CL.1a carbon steel, and their associated welds manufactured for primary coolant piping system of nuclear power plants. The effect of various parameters such as pipe size, welding method and chemical composition on the material properties were discussed. Test results showed that the offset of pipe size on tincture toughness was negligible, while the effect of welding method on fracture toughness was significant. In addition, Fracture toughness for carbon steel was influenced by silicon contents due to the different steel refining processes.
석창성(Chang-Sung Seok),김형익(Hyung-Ick Kim),장필수(Pil-soo Chang),주재만(Jae-Man Joo),강정훈(Jeong-Hoon Kang) 대한기계학회 2003 대한기계학회 춘추학술대회 Vol.2003 No.4
Most of the fatigue test were achieved in fully reversed condition that mean stress is zero. But,<br/> generally, mean stress can not be zero. This research was achieved the bending fatigue test that<br/> changes mean stress to spring steel and was studied relation with the mean stress and the fatigue life.<br/> The method to search effect about mean stress was extended S-N graph in two cases. One method was<br/> extended S-N graph using modified Miner's rule with considering damage. Another was extended using<br/> tendency of S-N graph. The exponential value(α) of mean stress-alternating stress equation is<br/> converged between the Goodman's and the Gerber's value even if fatigue life increases.
항공기용 복합재료의 충격후 잔류강도 예측 모델에 관한 연구
석창성(Chang-Sung Seok),최정훈(Jung-Hun Choi),박홍선(Hong-Sun Park),강민성(Min-Sung Kang),구재민(Jae-Mean Koo) 대한기계학회 2009 대한기계학회 춘추학술대회 Vol.2009 No.11
Damage induced by low velocity impact loading in aircraft composite is the form of failure which is occurred in aircraft. As the consequences of impact loading in composite laminates, matrix cracking, delamination and eventually fiber breakage for higher impact energies can be occurred. Even when no visible impact damage is observed, damage can exist inside of composite laminates and carrying load of the composite laminates is considerably reduced. The reduction of strength by impact occurs various loading during the flight. The objective of this study is to evaluate residual strength behavior of composite laminates by impact loading and to predict residual strength of impacted composite laminates. Impact and Tensile test was carried out on composite laminates made of woven CFRP.