• Elastomers and Composites
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• 제55권1호
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• pp.51-58
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• 2020

In this study, the thermal oxidation of raw natural rubber (NR) was investigated under controlled conditions by optical image and fourier transform infrared (FT-IR) analysis. The thermal oxidation was performed on a transparent thin film of raw NR coated on a KBr window in a dark chamber at 80℃ under low humidity conditions to completely exclude moisture and restrict light oxidation. Images of the thin film of raw NR were obtained before and after thermal oxidation. FT-IR absorption spectra were measured in the transmission mode at different thermal exposure times. The thermal oxidation of NR was examined by the changes in the absorption peaks at 3449, 1736, 1447, 1377, 1242, 1072, and 833 cm^-1, which corresponded to a hydroxyl group (-OH), a carbonyl group (-C=O) from an aldehyde and a ketone, a methylene group (-CH₂-), a methyl group (-CH₃), a carbon-oxygen single bond (-C-O) from an epoxide, a carbon-oxygen bond (-C-O) from an ether, an alcohol, a peroxide, or a cyclic peroxide, and a cis-methine group (cis-CCH₃=CH-), respectively. In the initial stage of thermal oxidation, two different types of free radicals were produced quickly and randomly by the homolytic cleavage of a double bond and allylic hydrogen abstraction. Aldehydes and ketones were formed from chain scissions of the double bonds and alcohols were produced from allylic hydrogen abstraction at the methylene or methyl groups. Two reactions seemed to proceed competitively with each other. At a later stage, oxidative crosslinks seemed to dominate through the combination of free radicals such as an allyl radical (CH=CHCH₂·), alkoxy radical (RO·), and peroxy radical (ROO·) and the reaction of a hydroperoxide (-ROOH) with a double bond. The image obtained after thermal oxidation showed hardening without cracks. Based on these observations, a plausible two-step mechanism was suggested for chain hardening caused by the thermal oxidation.

• 한국항공우주학회지
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• 제46권11호
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• pp.892-901
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• 2018

본 연구에서는 극초음속 비행체의 공력/열/탄성학적 거동을 반영할 수 있는 효율적인 공력 열하중 요소를 개발하였다. 빈번하게 설계 변경이 이루어지는 초기 설계 단계에서 효율적으로 사용될 수 있도록 준 해석적인 관계식을 적용하여 공력 하중과 열 하중을 구조 변형의 함수로 기술하고, 이를 기반으로 공력 열하중 요소를 정식화하였다. 정식화된 요소는 상용 프로그램의 사용자 서브루틴 형태로 구현하였으며, 이를 이용하여 극초음속 비행체 조종면의 공력/열/탄성학적 유한요소 연계해석을 수행하고 그 유용성을 확인하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.16-21
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• 2008

Aero-engine, as one kind of rotating machinery with complex structure and high rotating speed, has complicated vibration faults. Therefore, condition monitoring and fault diagnosis system is very important for airplane security. In this paper, a vibration data acquisition and intelligent fault diagnosis system is introduced. First, the vibration data acquisition part is described in detail. This part consists of hardware acquisition modules and software analysis modules which can realize real-time data acquisition and analysis, off-line data analysis, trend analysis, fault simulation and graphical result display. The acquisition vibration data are prepared for the following intelligent fault diagnosis. Secondly, two advanced artificial intelligent(AI) methods, mapping-based and rule-based, are discussed. One is artificial neural network(ANN) which is an ideal tool for aero-engine fault diagnosis and has strong ability to learn complex nonlinear functions. The other is data mining, another AI method, has advantages of discovering knowledge from massive data and automatically extracting diagnostic rules. Thirdly, lots of historical data are used for training the ANN and extracting rules by data mining. Then, real-time data are input into the trained ANN for mapping-based fault diagnosis. At the same time, extracted rules are revised by expert experience and used for rule-based fault diagnosis. From the results of the experiments, the conclusion is obvious that both the two AI methods are effective on aero-engine vibration fault diagnosis, while each of them has its individual quality. The whole system can be developed in local vibration monitoring and real-time fault diagnosis for aero-engine.

• 한국전산유체공학회지
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• 제19권1호
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• pp.47-56
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• 2014

Since a typical plate heat exchanger is made up of a huge number of unitary cells, it may be impossible to predict the aero-thermal performance of the full scale heat exchanger through three-dimensional numerical simulation due to the enormous amount of computing resources and time required. In the present study, a simple flow-network model using the friction factor correlation and a thermal-network model based on the effectiveness-number of transfer units (${\varepsilon}$-NTU) method has been developed. The complicated flow pattern inside the cross-corrugated heat exchanger has been modeled into flow and thermal networks. Using this model, the heat transfer between neighboring streams can be considered, and the pressure drop and the heat transfer rate of full-scale heat exchanger matrix are calculated. In the calculation, the aero-thermal performance of each unitary cell of the heat exchanger matrix was evaluated using correlations of the Fanning friction factor f and the Nusselt number Nu, which were calculated by unitary-cell CFD model.

• Advances in aircraft and spacecraft science
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• 제4권4호
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• pp.449-465
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• 2017

The aim of the present work is to present a computational study of the non-linear aero-elastic behavior of a multi-layered Thermal Protection System (TPS). The severity of atmospheric re-entry conditions is due to the combination of high temperatures, high pressures and high velocities, and thus the aero-elastic behavior of flexible structures can be difficult to assess. In order to validate the specific computational model and the overall strategy for structural and aerodynamics analyses of flexible structures, the simplified TPS sample tested in the 8' High Temperature Tunnel (HTT) at NASA LaRC has been selected as a baseline for the validation of the present work. The von $K{\acute{a}}rm{\acute{a}}n^{\prime}s$ three dimensional large deflection theory for the structure and a hybrid Raleigh-Ritz-Galerkin approach, combined with the first order Piston Theory to describe the aerodynamic flow, have been used to derive the equations of motion. The paper shows that a good description of the physical behavior of the fabric is possible with the proposed approach. The model is further applied to investigate structural and aero-elastic influence of the number of the layers and the stitching pattern.

• Composites Research
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• 제33권5호
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• pp.302-308
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• 2020

본 연구는 탄소 복합소재를 이용하여 오토클레이브와 진공백(Vacuum Bag Only) 공정으로 소재의 열전도 계수를구하고 경화 거동 모델을 통해 표면부와 내부의 경화 거동을 예측 및 비교하였다. 공정에 따른 열전도 계수의 변화로 인해 내부 온도가 표면부와 차이를 보였다. 오토클레이브 공정의 경우 높은 열전도 계수를 통하여 표면부와 내부의 온도는 거의 일치를 하였으며, 경화 거동 역시 유사하게 진행이 되었다. 하지만, 진공백 공정의 경우 표면부와 내부의 경화 거동이 많은 차이를 보였다. 이 차이는 부품 내부의 품질 및 공기 배출에 영향을 준다. 기계적 물성 차이를 확인하고자 0도 단방향 시편으로 압축시험을 수행하였고, 그 결과 진공백 성형이 조금 낮은 물성을 갖는다는 것을 확인하였다.

• 대한기계학회논문집 C: 기술과 교육
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• 제4권2호
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• pp.93-99
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• 2016

엔진 성능 혹은 효율의 극대화는 엔진 구성품들을 점점 더 극한의 환경에서 장시간 운용되게 요구하고 있다. 이를 위해 엔진 제작사 혹은 연구소는 초내열합금, 냉각 설계 최적화, 열차폐 코팅 개선 등의 노력과 동시에 재료 모델링, 유한요소해석, 최적설계 등의 수치 해석 기법을 적용하여 좀 더 정교한 설계 및 해석을 수행하고 있다. 본 연구에서는 연소기 뒤에 위치하는 1 단 고압터빈 노즐의 끝벽 냉각 설계와 열차폐 코팅에 따른 일방향 응고 재료인 1 단 고압터빈 블레이드의 저주기 피로 수명에 대한 영향을 고찰하고자 한다. 이를 위해 경계 조건인 고온 및 고압의 연소 가스에 의한 노즐 및 블레이드의 금속 온도는 복합 열 전달 해석을 통해 얻고, 이 결과를 받아 블레이드의 구조 해석 및 저주기 피로수명을 평가하여 노즐 냉각설계와 열차폐 코팅의 영향을 분석하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2011년도 제36회 춘계학술대회논문집
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• pp.465-465
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• 2011

Rolls-Royce is a global company producing advanced power systems for use on land, at sea and in the air. In order to develop competitive products and services, Rolls-Royce invests in technology, infrastructure and capability with much of the research carried out in a global network of University Technology Centres, such as the UTC in Thermal management at Pusan National University. Heat exchangers and thermal management play a critical role in today's gas turbine engines, maintaining the fuel and oil temperatures within the correct operational range. Future products are likely to place an increased duty on the thermal management system and thus require advances in heat exchanger design, installation and manufacturing. Heat exchangers further have the potential to play a vital role in Advanced Cycle Gas Turbine products. The Intercooled and recuperated WR21 marine gas turbine engine recently entered service with the Royal Navy and is delivering very attractive fuel burn in service. The development of an advanced cycle aero-engine is a significantly greater challenge, requiring better understanding of compact and light weight heat exchanger surfaces, novel installations and ducting systems and may required novel manufacturing techniques to achieve the volume, weight and cost necessary to realise a viable advanced cycle gas turbine aero-engine.

• 대한기계학회논문집B
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• 제38권11호
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• pp.915-924
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• 2014

항공기용 가스터빈 엔진에 있어서, 기어 어셈블리 및 전자장비에 사용되는 오일의 냉각을 위하여 열교환기가 사용되며 이를 Surface air-oil heat exchanger (SAOHE) 라고 한다. 이 열교환기는 엔진 팬 케이싱 내부에 설치되며 기어박스 시스템 및 전자장비로부터 바이패스 덕트 후류 쪽으로 열을 소산시킨다. 본 연구의 목적은 SAOHE 의 설계를 위한 효율적인 수치해석방법을 개발하는 것이다. SAOHE 설치에 따른 핀에서의 열공력학적 성능을 평가하기 위하여 다공성 모델을 활용한 2 차원 수치해석을 수행하였고, 열교환기 성능평가에 대해 시간 및 비용적으로 효과적인 1 차원 열유동 네트워크 프로그램을 개발하였다. 이 프로그램을 이용하여 열교환기의 압력강하 및 열전달 성능을 예측하였고, 1 차원 열유동 네트워크 프로그램을 검증하기 위해 2 차원 전산해석 결과 및 실험 결과와 비교하였다.

• 한국전산유체공학회지
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• 제10권1호
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• pp.16-23
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• 2005

The objective of this research is to estimate two dimensional ablating and charring of heat shield materials in severe aero-thermal heat transfer. This estimation requires an accurate and rapid technique for its serious heat transfer with a moving boundary. Aerodynamic heating is obtained by an explicit relation which is a function of Mach number and air condition, while a fully implicit method is used for heat transfer calculations. Moving boundary is captured by FLIAR method which is a subgroup of VOF. Thickness of ablating and charring of heat shield, temperature of the moving surface and rate of radiation heat are calculated and compared with references. The results are in good agreement with other calculations.