• 한국유체기계학회 논문집
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• 제15권5호
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• pp.27-31
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• 2012

Turbine inlet temperature is steadily increasing to achieve high specific thrust and efficiency of gas turbine engines. Turbine cooling technology is essential to increase turbine inlet temperature. For this study, a small or medium sized aircraft engine of 10,000 lbf class with the turbine inlet temperature of $1,400^{\circ}C$, the engine overall pressure ratio of 32.2, and the bypass ratio of 5 was set as the baseline model and its performance analysis was performed at the design point. The engine has the performance of 10,013 lbf thrust and the specific fuel consumption of 0.362 lbm/hr/lbf. The thrust and the specific fuel consumption of the baseline model were compared with those of similar class engines. Based on these results, the turbine design requirements were assigned. In addition, the parametric analysis of the engine, related to aerodynamic and cooling design of the high pressure turbine, was performed. Based on the baseline model engine, the influence of turbine inlet temperature, cooling flow ratio, and high pressure turbine efficiency variations on the engine performance was analyzed.

• 한국유체기계학회 논문집
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• 제16권6호
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• pp.32-39
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• 2013

In the present study, three-dimensional aerodynamic optimization of high pressure turbine nozzle for turbofan engine was performed. For this, Kriging surrogate model was built and refined iteratively by supplying additional experimental points until the surrogate model and CFX result has effective difference on objective function. When the surrogate model satisfied this reliability condition and developed enough, optimum point was investigated. Commercial program PIAnO was used for optimization process and evolutionary algorithm was used for searching optimum point. As a result, difference between estimated value from Kriging surrogate model and CFD result converges within 0.01% and the optimized nozzle shape has 0.83% improved aerodynamic efficiency.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 추계학술대회논문집
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• pp.812-817
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• 2005

The objective of the present work is to develop a time-domain numerical method of broadband noise in a cascade of airfoils. This paper focuses on dipole broadband noise sources, resulting from the interaction of turbulent inflows with the flat-plate airfoil cascade. The turbulence response of a two-dimensional cascade is studied by solving both of the linearised and full nonlinear Euler equations employing accurate higher order spatial differencing, time stepping techniques and non-reflecting inflow/outflow boundary condition. The time-domain result using the linearised Euler equations shows good agreement with the analytical solution using the modified LINSUB code. Through the comparison of the nonlinear time-domain result using the full nonlinear Euler equations with the linear, it is found that the acoustic mode amplitude of the nonlinear response is less than that of the linear response due to the energy cascade from low frequency components to the high frequency ones. Considering the merits of the time-domain methods over the typical time-linearised frequency-domain analysis, the current method is expected to be promising tools for analyzing the effects of the airfoil shapes, non-uniform background flow, linear-nonliear regimes on the broadband noise due to gust-cascade interaction.

• 농업생명과학연구
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• 제46권3호
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• pp.119-127
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• 2012

여름철 고온기 온실 내 효율적 증발냉방을 위하여 다량 포그 분무가 가능하고 설치비용이 저렴하도록 한 터보팬 2류체 노즐로 포그 분무장치를 구성하고 소형 유리온실에 2.2 m 높이로 설치하여 냉방시험을 실시하였다. 이 장치의 분무시험 결과 평균분무입경이 $29{\mu}m$이고 1대당 포그 분무량은 $160m{\ell}/min$로 비산반경 2 m이내에서 입자들이 모두 증발하는 것으로 나타났다. 이 장치를 평면적 $228m^2$인 단동 유리온실에 2대를 설치하여 냉방실험한 결과, 외기의 온도 $30.2^{\circ}C$, 상대습도 81.2%인 때 온실 내 공기의 온도 $28.8^{\circ}C$, 상대습도 87.5%의 낮은 냉각효과를 나타내었다. 문헌 조사와 냉방실험 결과로부터 여름철 우리나라 남부지역의 외기온 $35^{\circ}C$를 기준으로 단동온실은 50% 차광에서 증발냉각에 의해 온실 내 공기온도를 외기온보다 $2{\sim}3^{\circ}C$ 낮추려면 환기회수 1회/분, 물분무량은 $10m{\ell}/min/m^2$인 것으로 추정되었다.

• 한국유체기계학회 논문집
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• 제17권5호
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• pp.43-53
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• 2014

This paper presents a the study on air curtain system of top and bottom bi-directional jet air discharge for blocking the spread of smoke in case of tunnel fire. The five kinds different air curtains of A, B, C, D, and E of models for various performance tested after manufactured. A results of the various performance test obtained the best efficiency from E model air curtain. And optimize the injection angle of the air curtain nozzle through the three-dimensional computational fluid dynamics (CFD) analysis and analyzed the effects of external pressure of tunnel. and also single factor design have been applied. At present, our attention is focused on the velocity distribution(flow width and flow position) of 1.5m on the ground in tunnel. Also, analyzed the influence of draft in the tunnel. Detailed effects of discharge angle of air curtain and velocity at nozzle exit are discussed.

• 항공우주산업기술동향
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• 제7권1호
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• pp.11-19
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• 2009

지역 내에서 주로 운항되는 중형항공기 시장은 2001년 이후 전반적인 세계경기 회복기조 속에서 꾸준한 성장을 이어왔으나, 2007년 말 경부터 이어진 세계적인 불경기는 현재 그 미래를 혼란스럽게 하고 있다. 현재까지 리저널 항공기 산업은 항공기의 대형화와 리저널 젯의 확산이 주요 시장 동향으로 나타나고 있었다. 그러나, 유가 급등이나 세계 경제 침체와 같은 상황적 변화는 세계 항공사에 경제적인 타격을 가져왔으며 특히, 1990년대 ERJ-145의 성공으로 중형항공기의 주류를 이루었던 터보젯 기에 대한 회의적인 시각과 함께, 잊혀져가던 터보프롭 중형기가 새로이 주목받기도 하는 등 이는 다시 항공기 제작사 및 이들의 개발 계획에 큰 영향을 끼쳤다. 이에 따라 비록 현재 진행 중인 신규 항공기 개발 계획은 여전히 터보젯 기종이 주를 이루고 있으나, 여러 시장 전망 자료에서는 향후 시장에서 터보프롭기의 비중을 늘리고 있는 현실이다. 본 고에서는 여러 시장 전망 자료를 바탕으로 향후 중형항공기 시장의 변화 방향에 대하여 논하였다.