• 한국항공운항학회지
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• 제30권1호
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• pp.12-19
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• 2022

The exhaust wake of an aircraft engine is discharged in a high temperature and high speed, which can damage objects such as an aircraft in the rear. The exhaust wake can lift small foreign substances lying on the ground or falling off, and the floating foreign substances can enter the intake duct of the aircraft moving from the rear and cause engine FOD (Foreign Object Damage). This study experimentally analyzed how the engine exhaust wake generated from military jet fighters affects the movement of foreign substances and evaluated the effects of foreign substances on the damaged area by measuring wake velocity. The simulation and field experimental results confirmed that the effect of exhaust wake increases as the rear position closer, and that foreign substances lifted by the wake can act as FOD to the adjacent rear aircraft.

• Journal of Mechanical Science and Technology
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• 제15권10호
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• pp.1423-1433
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• 2001

A flow modeling method has been developed to analyze the flow in the annular base (rear- facing surface) of a circular engine nacelle flying at subsonic speed but with a supersonic exhaust jet. Real values of exhaust gas properties and temperature at an altitude of 30, 000 feet are employed. Potential flows of the air and gas streams are computed for the flow past a separated wake. Then a viscous jet mixing is superimposed on this inviscid solution. Conserva- tion of mass, momentum and energy for the wake flow field is achieved by multiple iterations with modest computer requirements.

• 한국가시화정보학회지
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• 제10권1호
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• pp.47-54
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• 2012

Single Stage To Orbit (SSTO) missions which require its engines to be operated at varying back pressure conditions, use engines operate at high combustion chamber pressures (more than 100bar) with moderate area ratios (AR 70~80). This ensures that the exhaust jet flows full during most part of the operational regimes by optimal expansion at each altitude. Aero-spike nozzle is a kind of altitude adaptation nozzle where requirement of high combustion chamber pressures can be avoided as the flow is adapted to the outside conditions by the virtue of the nozzle configuration. However, the thrust prediction using the conventional thrust equations remains to be a challenge as the nozzle plume shapes vary with the back pressure conditions. In the present work, the performance evaluation of a new aero-spike nozzle is being carried out. Computational studies are carried out to predict the thrust generated by the aero-spike nozzle in varying back pressure conditions which requires the unsteady pressure boundary conditions in the computational domain. Schlieren pictures are taken to validate the computational results. It is found that the flow in the aero-spike nozzle is mainly affected by the base wall pressure variation. The aerospike nozzle exhibits maximum performance in the properly expanded flow regime due to the open wake formation.

• 한국산업정보학회논문지
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• 제28권6호
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• pp.99-105
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• 2023

고도의 생존성이 요구되는 잠수함은 군의 전략자산에서 가장 중요한 전투 무기체계 중 하나이다. 일반적인 재래식 잠수함은 추진시스템을 작동하기 위해 공기가 필요해 필연적으로 스노클 항해를 하며 잠수함 내부로 공기를 공급해야 한다. 그리고 스노클 항해 시 수중으로 배출된 폐기 가스는 주변 유체를 가열해 온도 항적을 형성하고 결과적으로 잠수함의 생존성을 감소시킨다. 본 연구에서는 수중 잠수함의 폐기로 인해 형성된 수면의 온도 항적에 관한 기초 실험 연구를 수행하였다. 이를 위해 국내 도입된 잠수함의 추진시스템과 항해 조건 자료를 수집하였으며, 온도 항적을 계측하기 위한 실험 시스템을 구현하였다. 실험 결과 수조로 주입된 고온 기포는 작은 크기로 부서져 주위를 둘러싼 유체와 유사한 수준으로 온도가 감소하였으며, 이를 열전대 센서로 확인하였다. 그리고 수면의 온도 항적을 계측하기 위한 열화상 시스템의 결과에서도 온도 항적은 계측되지 않았다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 추계학술대회논문집B
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• pp.491-496
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• 2000

The physics of the flow field surrounding an engine nacelle afterbody is very complex. A high pressure jet from the nozzle interacts with the external flow and causes upstream influence on the afterbody surface field. At certain conditions, the nozzle boundary layer can separate, either by shock wave interaction or by adverse pressure gradient effect, resulting in a severe drag penalty. Furthermore, a finite afterbody base implies a recirculating flow region. A flow modeling method has been developed to analyze the flow in the annular base(rear-facing surface) of a circular engine nacelle flying at subsonic speed but with a supersonic exhause jet. Real values of exhaust gas properties and temperature are included.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 춘계학술대회논문집
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• pp.1010-1015
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• 2002

Over the last few decades, noise has played a major role in the development of aircraft engines. The dominant noise is generated by the wake interactions of fan and downstream stator. Engine inlet and exhaust ducts are being fitted with liner materials that aid in damping fan related noise. In this paper, the radiation of duct internal noise from duct open ends with liners is studies via numerical methods. The linearized Euler's equations in generalized curvilinear coordinates are solved by the DRP scheme. The far field sound pressure levels are computed by the Kirchhoff integration method. Through comparison of sound directivity from bell-mouth duct with and without liners, it is shown that radiation from engine inlet is affected by liner effects or a soft wall boundary condition.

• Asia Marketing Journal
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• 제16권1호
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• pp.229-241
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• 2014

In 1997 the Asian Foreign Currency Crisis hit Korean shores. In its wake, Korean consumers demanded cost-saving solutions which will increase both the use-life and the fuel efficiency their vehicles. Bullsoneshot's effects include increases in gas mileage as well as cleaner cylinders, intakes and exhaust valves, the product was welcomed by an explosive demand from people driving older cars in an adverse economy. The history of Bullsone can be categorized as two major stages. The First stage is lunching era of "Bullone Shot" following competitor brand. The second stage is extension stage of brand and line based on Bullsone's positive brand equity. Mr. Hyun Woo Shin, formal CEO of OXY inc. and also formal vice president of OCI (Oriental Chemical Industries) take charge of New CEO of Bullsone. He energetically push the Bullsone's family brands and got a desirable results. He also setup ambitious goal : reach 100bn KRW in gross sales within 3 years. "Ripping itself free from 30~40 bn KRW sales range in which the company has stagnated in the last 10 years, Bullsone intends to be aggressive enough in marketing to reach 150 bn KRW in sales in 2013, and reach 700 bn KRW by 2018." This is the goal iterated by Bullsone's top executive team.

• 한국화재소방학회논문지
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• 제30권5호
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• pp.74-81
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• 2016

본 연구의 목적은 원자력발전소 주제어실 화재시 운전원의 거주성을 평가하는 것이다. 운전원의 거주성 분석을 위해 FDS v.6.0을 사용하였으며 이를 통해 주제어실 화재 시 배연성능과 운전원의 거주성에 있어 도출되는 문제점을 확인하였다. 본 연구에서는 공조환기설비의 운전조건을 핵심변수로 지정하고 그에 따라 3가지 시나리오로 분류하였다. 수치해석결과, Case 1(공조설비 작동시)의 경우가 연기온도, 복사열, 광학밀도 및 연기층높이에 의한 영향이 가장 심각한 것으로 나타났다. 이에 반해, Case 2(공조설비 미작동시)와 Case 3(공조설비 미작동시 풍량 1.5배 증가 시)는 Case 1보다 더 안전한 것으로 나타났다. 약 820초경 연기온도를 확인한 결과, Case 1이 Case 2와 Case 3보다 약 63% 정도 더 높게 나타났다. 복사열에 의한 영향도 Case 1에서 가장 높게 나타나, Case 2 및 Case 3와는 최대 약 68% 이상의 차이를 보였다. 분석결과를 통해, 주제어실의 공조환기설비는 배연성능에 큰 영향을 미쳐 운전원 거주안전을 지키기 위한 주요 인자인 것을 확인하였다. 다만, 급기구와 배연구가 천정부에 동시에 설치되어 있어 Case 2와 Case 3의 경우 연기층높이에 있어 불연속적 패턴을 나타냈다.

• Nuclear Engineering and Technology
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• 제55권10호
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• pp.3874-3897
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• 2023

A high-fidelity computational fluid dynamics (CFD) analysis was performed using the Large Eddy Simulation (LES) model for the lower plenum of the High-Temperature Test Facility (HTTF), a ¼ scale test facility of the modular high temperature gas-cooled reactor (MHTGR) managed by Oregon State University. In most next-generation nuclear reactors, thermal stress due to thermal striping is one of the risks to be curiously considered. This is also true for HTGRs, especially since the exhaust helium gas temperature is high. In order to evaluate these risks and performance, organizations in the United States led by the OECD NEA are conducting a thermal hydraulic code benchmark for HTGR, and the test facility used for this benchmark is HTTF. HTTF can perform experiments in both normal and accident situations and provide high-quality experimental data. However, it is difficult to provide sufficient data for benchmarking through experiments, and there is a problem with the reliability of CFD analysis results based on Reynolds-averaged Navier-Stokes to analyze thermal hydraulic behavior without verification. To solve this problem, high-fidelity 3-D CFD analysis was performed using the LES model for HTTF. It was also verified that the LES model can properly simulate this jet mixing phenomenon via a unit cell test that provides experimental information. As a result of CFD analysis, the lower the dependency of the sub-grid scale model, the closer to the actual analysis result. In the case of unit cell test CFD analysis and HTTF CFD analysis, the volume-averaged sub-grid scale model dependency was calculated to be 13.0% and 9.16%, respectively. As a result of HTTF analysis, quantitative data of the fluid inside the HTTF lower plenum was provided in this paper. As a result of qualitative analysis, the temperature was highest at the center of the lower plenum, while the temperature fluctuation was highest near the edge of the lower plenum wall. The power spectral density of temperature was analyzed via fast Fourier transform (FFT) for specific points on the center and side of the lower plenum. FFT results did not reveal specific frequency-dominant temperature fluctuations in the center part. It was confirmed that the temperature power spectral density (PSD) at the top increased from the center to the wake. The vortex was visualized using the well-known scalar Q-criterion, and as a result, the closer to the outlet duct, the greater the influence of the mainstream, so that the inflow jet vortex was dissipated and mixed at the top of the lower plenum. Additionally, FFT analysis was performed on the support structure near the corner of the lower plenum with large temperature fluctuations, and as a result, it was confirmed that the temperature fluctuation of the flow did not have a significant effect near the corner wall. In addition, the vortices generated from the lower plenum to the outlet duct were identified in this paper. It is considered that the quantitative and qualitative results presented in this paper will serve as reference data for the benchmark.