• 산업경영시스템학회지
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• 제41권3호
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• pp.186-193
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• 2018

Modern manufacturing industries is to produce both precise and robust mechanical parts without failure while they are in service. In order to prevent a part failure for its lifetime, a mechanical design for a part should be examined on a basis of mechanical simulation. A nozzle plate, being a key part in steam engines, changes flow directions of steam in a turbine used in power plant. This paper is to the design and test for part safety and durability. Currently, nozzle plates are fabricated by welding nozzles to their plates. Welding causes some defects on the used materials while they are being manufactured. Another major defect is un-even pitches between welded nozzles. Welding causes phase changes because of high melting temperature of metal. This leads to decay on the welding spots, which weakens their structural strength and then, may lead to early damages on mechanical structures. This research proposes assembly-typed nozzle plate without welding. From the beginning, nozzle and plate are designed for insertion-typed assembly. Nozzle head and foot are designed in accordance with the grooves on outer ring and inner ring of a plate to make mating surfaces. Then the nozzle plate should be proved for structural and fatigue safety before they are put in manufacturing. This research adopts commercial softwares for modeling and mechanical simulation. The test result shows that the design with smaller mating area and deeper insertion produces higher safety in terms of structure and durability. From the conclusion, this paper proposes the assembly-typed nozzle plate to replace the welding typed.

• Transactions on Electrical and Electronic Materials
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• 제16권6호
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• pp.317-322
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• 2015

The metal oxide varistor (MOV) is a major component of the surge protection devices (SPDs) currently in use. The device is judged to be faulty when fatigue caused by the continuous inflow of lightning accumulates and reaches the damage limit. In many cases, induced lightning resulting from lightning strikes flows in to the device several times per second in succession. Therefore, the frequency or the rate at which the SPD is actually exposed to stress, called a surge, is outside the range of human perception. For this reason, the protective device should be replaced if it actually approaches the end of its life even though it is not faulty at present, currently no basis exists for making the judgment of remaining lifetime. Up to now, the life of an MOV has been predicted solely based on the number of inflow surges, irrespective of the magnitude of the surge current or the amount of energy that has flowed through the device. In this study, nonlinear data that shows the damage to an MOV depending on the count of surge and the amount of input current were collected through a high-voltage test. Then, a failure prediction algorithm was proposed by preparing a look-up table using the results of the test. The proposed method was experimentally verified using an impulse surge generator

• 대한인간공학회지
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• 제15권2호
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• pp.25-36
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• 1996

The purposes of the present study were: (1) to investigate aeromedical dissorders prevalent among ROK air force pilots and (2) to evaluate their detrimental effects on flight performance. The study examined the eight flight-induced disorders primarily responsible for permanent grounding and flying restrictions. According to the survey of 600 randomly selected pilots, 80.2% of the respondents have experienced low back pain, which was 20% higher than the lifetime prevalence in Swedish male workers. Bradyacusia ranked second (56.0%) resulting from continuous exposure to high aircraft noise. The cardiovascular disorders, the most common cause for permanent grounding of Canadian forces pilots, were found in 16.0% of the Korean pilots. Due to the high prevalence of the disorders, in 1993 the Korean pilots received medical treatments 10 times as many as factory workdes. Compared to the flight performance of Israeli and British pilots in wars, the flight performance of the Korean pilots was found to be inferior. Such poor performance can be attributable to the high incidence rates of disorders. Statistical analyses revealed that the aeromedical disorders were related to personal variables such as age, flight career- related factors, and fatigue. Cigarette smoking and drinking habit contributed to worsening back pain, barotitis media, and pulmonary disorders. More comprehensive research was recommended to identify health hazards, combined with intervention to minimize disorders that could lead to early termination of flight careers or excessive loss of flight time. This study further suggests that aeromedical institutions in Korean air force should be fostered more professionally and financially.

• 대한기계학회논문집A
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• 제27권8호
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• pp.1388-1397
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• 2003

Since the reliability of adhesively bonded joints for composite structures is dependent on many parameters such as the shape and dimensions of joints, type of applied load, and environment, so an accurate estimation of the fatigue life of adhesively bonded joints is seldom possible, which necessitates an in-situ reliability monitoring of the joints during the operation of structures. In this study, a self-sensor method for adhesively bonded joints was devised, in which the adhesive used works as a piezoelectric material to send changing signals depending on the integrity of the joint. From the investigation, it was found that the electric charge increased gradually as cracks initiated and propagated in the adhesive layer, and had its maximum value when the adhesively bonded joint failed. So it is feasible to monitor the integrity of the joint during its lifetime. Finally, a relationship between the piezoelectric property of the adhesive and crack propagation was obtained from the experimental results.

• International Journal of Naval Architecture and Ocean Engineering
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• 제6권4호
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• pp.983-999
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• 2014

The structural design of the ships includes two main issues which should be checked carefully, namely the extreme structural response (yielding & buckling) and the fatigue structural response. Even if the corresponding failure modes are fundamentally different, the overall methodologies for their evaluation have many common points. Both issues require application of two main steps: deterministic calculations of hydro-structure interactions for given operating conditions on one side and the statistical post-processing in order to take into account the lifetime operational profile, on the other side. In the case of ultra large ships such as the container ships and in addition to the classical quasi-static type of structural responses the hydroelastic structural response becomes important. This is due to several reasons among which the following are the most important: the increase of the flexibility due to their large dimensions (Lpp close to 400 m) which leads to the lower structural natural frequencies, very large operational speed (> 20 knots) and large bow flare (increased slamming loads). The correct modeling of the hydroelastic ship structural response, and its inclusion into the overall design procedure, is significantly more complex than the evaluation of the quasi static structural response. The present paper gives an overview of the different tools and methods which are used in nowadays practice.

• 한국주조공학회지
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• 제26권4호
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• pp.180-183
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• 2006

NICI재의 미세조직 및 기계적 성질에 미치는 Ni 첨가원소의 영향을 연구하였다. 선재공장의 열간압연롤재로서의 NICI재는 내열 피로크랙성, 경도값, 인장성질, 내마모성이 매우 중요하다. 주방상태에서 4% Ni 첨가로 주요 기지상인 퍼얼라이트상이 베이나이트상으로 변화되었다. 베이나이트상을 주요 기지상으로 가지는 4% Ni 첨가 NICl재는 퍼얼라이트상을 주요 기지상으로 가지는 통상의 NICI재에 비해서 경도값(HRC 48) 및 인장강도값($72\;kg/mm^2$)이 우수하였으며, 이는 선재압연롤 재료로서 우수한 성능을 발휘할 수 있을 것으로 예측된다.

• 한국재료학회지
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• 제25권10호
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• pp.571-576
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• 2015

The effects of coating thickness on the delamination and fracture behavior of thermal barrier coating (TBC) systems were investigated with cyclic flame thermal fatigue (FTF) and thermal shock (TS) tests. The top and bond coats of the TBCs were prepared by electron beam-physical vapor deposition and low pressure plasma spray methods, respectively, with a thickness ratio of 2:1 in the top and bond coats. The thicknesses of the top coat were 200 and $500{\mu}m$, and those of the bond coat were 100 and $250{\mu}m$. FTF tests were performed until 1140 cycles at a surface temperature of $1100^{\circ}C$ for a dwell time of 5 min. TS tests were also done until more than 50 % delamination or 1140 cycles with a dwell time of 60 min. After the FTF for 1140 cycles, the interface microstructures of each TBC exhibited a sound condition without cracking or delamination. In the TS, the TBCs of 200 and $500{\mu}m$ were fully delaminated (> 50 %) within 171 and 440 cycles, respectively. These results enabled us to control the thickness of TBC systems and to propose an efficient coating in protecting the substrate in cyclic thermal exposure environments.

• Advances in aircraft and spacecraft science
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• 제8권4호
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• pp.289-302
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• 2021

Ensuring flight safety for passengers as well as crew is the most important aspect of modern aviation, and in order to achieve this, it is necessary to be able to forecast the durability of individual components. The present contribution illustrates the results of a computational analysis to determine the possibility of analysing the prediction of bearing durability in on-board rotating equipment from the point of view of thermal fatigue.In this study, a method developed at the Air Force Institute of Technology was used for analysis, which allowed to determine the bearing durability from the flight altitude profile. Two aircraft have been chosen for analysis - a military M-28 and a civilian Embraer. As a result of the analysis were obtained: the bearing durability in on-board rotating devices, average operation time between failures, as well as failure rate. In conclusion, the practical applicability of this approach is demonstrated by the fact that even with a limited number of flight parameters, it is possible to estimate bearing durability and increase flight safety by regular inspections.

• 대한기계학회논문집A
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• 제38권10호
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• pp.1185-1191
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• 2014

가스터빈 블레이드는 증기터빈 블레이드와 달리 냉각홀 및 냉각유로를 포함한 복잡한 형상으로 되어 있으며 복합화력의 운전특성에 따라 반복적이거나 지속적인 열-기계 하중 조건 하에서 운전된다. 따라서 블레이드는 운전시간에 따라 균일하지 못한 온도 분포나 응력 분포를 보이며, 이는 크리프나 열-기계피로 손상을 유발하며, 결국 가스터빈 블레이드의 수명을 단축시킨다. 결국 다양한 운전 조건에 따라 발생하는 응력을 정확하게 계산하는 것은 설비의 신뢰성을 보장하고 나아가 블레이드와 같은 고온 부품의 정확한 수명을 평가하는데 무엇보다 중요하다. 최근 들어 컴퓨터 기능이 좋아지고 상용 소프트웨어의 성능이 향상되어 실증 시험에 대한 대안으로 유동, 열 및 구조해석을 연결하는 전산해석이 많이 사용되고 있다. 본 논문에서는 가스터빈 실 운전조건을 고려하여 유동-열-구조 해석 기법을 연계하는 유체-구조 연성해석을 통해 블레이드 온도 및 응력분포를 계산하였다. 또한 해석 결과를 토대로 대표적인 손상기구인 크리프 및 열-기계 피로 손상 모델을 이용하여 블레이드의 수명을 평가하였다.

• Nuclear Engineering and Technology
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• 제42권6호
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• pp.662-669
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• 2010

To develop the manufacturing methods for the blanket first wall (FW) of the International Thermonuclear Experimental Reactor (ITER) and to verify the integrity of the joint, Be/Cu mockups were fabricated and tested at the KoHLT-1 (Korea Heat Load Test facility), a graphite heater facility located at the Korea Atomic Energy Research Institute (KAERI). Since Be and Cu joining is the focus of the present study, the fabricated mockups had a CuCrZr heat sink joined with three Be tiles as an armor material, unlike the original ITER blanket FW, which has a stainless steel structure and coolant tubes. Hot isostatic pressing (HIP) was carried out at $580^{\circ}C$ and 100 MPa for 2 hours as the method for Be/Cu joining. Three interlayers, namely, $1{\mu}mCr/10{\mu}mCu$, $1{\mu}mTi/0.5{\mu}mCr/10{\mu}mCu$, and $5{\mu}mTi/10{\mu}mCu$ were applied as a coating to the Be tiles by a physical vapor deposition (PVD) method. A shear test was performed with the specimens, which were fabricated by the same methods as those used to fabricate the mockups. The average values were 125 MPa to 180 MPa, and the samples with the $1{\mu}mCr/10{\mu}mCu$ interlayer showed the lowest value. No defect or delamination was found in the joints of the mockups by the developed ultrasonic test using a flat-type probe with a 10 MHz frequency and a 0.25 inch diameter. High heat flux (HHF) tests were performed at $1.0\;MW/m^2$ heat flux for each mockup using the given conditions, and the results were analyzed by ANSYS-CFX code. For the test criteria, an expected fatigue lifetime about 1,000 cycles was obtained by analysis with ANSYS-mechanical code. Mockups using the interlayers of $1{\mu}mTi/0.5{\mu}mCr/10{\mu}mCu$ and $5{\mu}mTi/10{\mu}mCu$ survived up to 1,100 cycles over the required number of cycles. However, one of the Be tiles in the other two mockups using the $1{\mu}mCr/10{\mu}mCu$ interlayer was detached during the screening test, and others were detached by discharge after 862 cycles. The integrity of the joints using the proposed interlayers was proven by the HHF test, but the other interlayer requires more study before it can be used for the joining of Be to Cu. Moreover, it was confirmed that the measured temperatures agreed well with the analysis temperatures, which were used to estimate the lifetime and that the developed facility showed its capability of the long time operation.