• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 춘계학술대회논문집B
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• pp.520-524
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• 2000

A ejector system is one of the fluid machinery, which has been mainly used as an exhaust pump or a vacuum pump. The ejector system has often been pointed out to have only a limited efficiency because it is driven by pure shear action and the mixing action between primary and secondary streams. In the present work, numerical simulations were conducted to investigate the effects of the geometry and the mass flow ratio of supersonic ejector-diffuser systems on their mixing performance. A fully implicit finite volume scheme was applied to solve the axisymmetric Navier-Stokes equations, and the standard ${\kappa}-{\varepsilon}$ turbulence model was used to close the governing equations. The flow fields of the supersonic ejector-diffuser systems were investigated by changing the ejector throat area ratio and the mass flow ratio. The existence of the second throat strongly affected the shock wave structure inside the mixing tube as well as the spreading of the under-expanded jet discharging from the primary nozzle, and served to enhance the mixing performance.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.627-630
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• 2009

이젝터 시스템은 주유동 제트에 발생되는 전단 응력과 압력차에 의해 흡입 챔버 압력에 영향을 미치거나 이차 흡입 유동을 유도한다. 이젝터는 터빈 기반 복합사이클 추진기관 및 로켓엔진의 고고도 모사 설비, 압력회복장치, 담수화 시스템, 이젝터 램젯시스템과 같이 많은 분야에 적용되어 널리 사용된다. 본 연구에서는 아음속 및 음속 조건에서 작동하는 이젝터의 형상 및 운전 조건을 결정하는 설계 절차를 수립하고자 하였다. 또한, 이론적 방법과 시험적 연구를 통해 축소 확대 디퓨저가 장착된 이젝터의 작동 특성을 파악하였다. 결국, 수치해석을 통해 요구 성능을 만족하는 이젝터의 최적 형상을 결정하였으며 다양한 노즐 목 및 챔버 직경을 변화시킨 이젝터에 대한 성능 시험을 통해 계산 결과를 검증하였다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 춘계학술대회
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• pp.1771-1776
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• 2003

The supersonic swirl jet is being extensively used in many diverse fields of industrial processes since those lead to more improved performance, compared with the conventional supersonic no swirl jet. In the present study, an experiment is carried out to investigate the effect of annular swirl jet on the supersonic dual coaxial jet. A convergent-divergent nozzle with a design Mach number of 1.5 is used for the supersonic primary jet, and the sonic nozzles with four tangential inlets are used to make the secondary swirl jet. The primary jet pressure ratio is varied in the range from 3.0 to 7.0 and the outer annular jet pressure ratio is from 1.0 to 4.0. The interactions between the annular swirl and the inner supersonic jet are quantified by the pitot impact and static pressure measurements and visualized by using the Schlieren optical method. The results show that annular swirl jet alters the shock structure and impact pressure distributions compared with no swirl jet.

• 대한기계학회논문집B
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• 제29권8호
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• pp.934-939
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• 2005

Starting pressure of a supersonic ejector with a second-throat was investigated. In case of mixing chamber length longer than a critical length, starting pressure is in proportion to length of the mixing chamber. In this study, we assumed that the ejector starts when the primary supersonic flow reaches inlet of the second-throat and the distance of the supersonic flow traveling can be expressed by multiplying an empirical factor to the first diamond shock length of overexpanded flow. To calculate the overexpanded supersonic flow, a mixing model was employed to compute secondary flow pressure and the result was applied to back pressure condition of overexpanded flow calculation. In the result, for three cases of primary nozzle area ratio, we could get accurate model of predicting the starting pressure by selecting a suitable empirical factors around 3.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.37-40
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• 2003

The thrust vector control using a fluidic counterflow concept is achieved by applying a vacuum to a slot adjacent to a primary jet which is shrouded by a suction collar. The vacuum produces a secondary reverse flowing stream near the primary. The shear layers between the two counterflowing streams mix and entrain mass from the surrounding fluid. The presence of the collar inhibits mass entrainment and the flow m the collar accelerates causing a drop in pressure on the collar. For the vacuum asymmetrically applied to one side of the nozzle, the jet will vector toward the low-pressure region. The present study is performed to investigate the effectiveness of thrust vector control using the fluidic counterflow concept. A computational work is carried out using the two-dimensional, compressible Navier-Stokes equations, with several kinds of turbulence models. The computational results are compared with the previous experimental ones. It is found that the present fluidic counterflow concept is a viable method to vector the thrust of a propulsion system.

• 한국추진공학회지
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• 제5권3호
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• pp.33-40
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• 2001

본 연구에서는 초음속 증기 이젝터의 작동특성을 조사하기 위하여 압축성 축대칭 Navier-Stokes 방정식의 수치계산을 행하였다. 2차 유동측의 압력 및 배압을 변화시켜 이들 압력이 혼입유량에 미치는 영향을 조사하였다. 연구의 결과로부터 초음속 증기 이젝터에서 2차 유동측 압력 및 배압은 임계 혼입유량에 상당한 영향을 미치며, 1차구동노즐의 형상과 2차유동의 압력이 주어지는 경우 임계혼입 유량비를 예측할 수 있음을 알았다. 수치계산 결과는 실험에서 얻은 임계혼입유량비를 잘 예측하였다.

• 한국추진공학회지
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• 제4권4호
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• pp.1-8
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• 2000

본 연구에서는 아음속/초음속 이젝터 시스템의 효과적인 설계를 목적으로, 증기 보일러로부터 발생하는 파열증기를 1차 구동유체로 하는 축대칭 아음속/초음속 이젝터 유동을 실험하였다. 과열증기는 여러형태의 아음속/초음속 노즐에 의하여 이젝터 혼합부로 방출되도록 설계되었으며, 2차정체실 내부에 있는 대기 공기는 증기제트에 의하여 혼합부로 유입된다. 실험에서는 2차정체실의 진공성능을 조사하기 위하여 넓은 범위의 이젝터 자동압력비에 대하여 적용하였다. 본 연구의 결과로부터 이젝터목에서 혼한유동의 정압은 1차 노즐의 형태에 관계없이 이젝터 작동압력비의 함수만에 의하여 결정된다는 것을 알았다.

• Nuclear Engineering and Technology
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• 제55권10호
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• pp.3549-3558
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• 2023

The jet pump can be used in a test device of a nuclear reactor for high flow amplification as it reduces inlet flow requirement and thereby size of the process components. In the present work, a miniature jet pump was designed to meet high flow amplification greater than 3. Subsequently, experiments were carried out using a test setup for design validation and performance evaluation of the jet pump for different parameters. It was observed that a minimum pressure of 0.6 bar (g) was required for the secondary fluid inside the jet pump to ensure cavitation free performance at high amplification. Spacing between the nozzle tip and the mixing chamber entry point had significant effect on the performance of the jet pump. Variation in primary flow, temperature and area ratio also affected the performance. It was observed that at high flow amplification, the analytical solution differed significantly from experimental results due to very large velocities encountered in the miniature size jet pump.

• 한국응용과학기술학회지
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• 제30권2호
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• pp.320-332
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• 2013

소각로 내 공기 주입은 연소가스의 체류시간, 미연분 제거 및 출구가스 온도 제어 등의 많은 영향을 끼친다. 이에 따라 2차 연소용 공기량을 변화시켜 충분한 체류시간을 확보하고 $850^{\circ}C$ 이상의 출구가스 온도를 유지하며, 높은 turbulent를 관리함으로써 안정적인 소각로 운영이 되어야만 한다. 본 연구에서는 현재 운영 중인 소각장의 소각로를 설계하고, 평균 일일 소각량을 바탕으로 1차 공기량을 산정한 후 2차 공기량을 변화하여 CFD 프로그램(Fluent)을 통해 이론적인 공기유동을 규명하였다. 또한 산정된 공기량을 바탕으로 실제 운영 중인 소각장에 적용함으로써 최적의 연소조건을 도출하였다. CFD simulation 결과 1.2차 공기비는 75:25가 최적의 결과로 나타났으며, 2차 공기 분사노즐 전 후면 유속 비는 1:3에서 가장 우수한 결과로 나타났다. 또한, 실제 운영 중인 소각로에 적용한 결과 적절한 소각로 출구온도는 질소산화물 제거 효율 및 일산화탄소 발생농도에 영향을 미치는 것으로 나타났다.

• 대한기계학회논문집
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• 제18권7호
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• pp.1789-1798
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• 1994

This paper aimed for numerical simulation of complicated gas turbine combustor with swirler. For the convenience of numerical analysis, fuel nozzle and air linear hole areas of secondary and dilution zone, which are issued to jet stream, were simplified to equivalent areas of annular type. In other to solve these problems, imaginary source terms which are corresponded to supplied fuel amount were added to those of governing equation. Chemical equilibrium model of infinite reaction rate and $k-{\epsilon}-g$ model with the consideration of density fluctuation were applied. As the result, swirl intensity contributed to mixing of supplied fuel and air, and to speed up the flame velocity than no swirl condition. Temperature profiles were higher than experimental results at the upstream and lower at the downstream, but total energy balance was accomplished. As these properties showed the similar trend qualitatively, simplified simulation method was worth to apply to complicated combustor for predicting combustion characteristics.