• 한국자동차공학회논문집
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• 제10권5호
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• pp.81-89
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• 2002

The autoignition and subsequent flame propagation of initially nonpremixed turbulent system have been numerically analyzed. The unsteady flamelet modeling based on the RIF (representative interactive flamelet) concept has been employed to account for the influences of turbulence on these essentially transient combustion processes. In this RIF approach, the partially premixed burning, diffusive combustion and formation of pollutants(NOx, soot) can be consistently modeled by utilizing the comprehensive chemical mechanism. To treat the spatially distributed inhomogeneity of scalar dissipation rate, the multiple RIFs are employed in the framework of EPFM(Eulerian particle flamelet model) approach. Computations are made for the various initial conditions of pressure, temperature, and fuel composition. The present turbulent combustion model reasonably well predicts the essential features of autoignition process in the transient gaseous fuel jets injected into high pressure and temperature environment.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2006년도 추계 학술대회논문집
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• pp.185-188
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• 2006

An investigation of the ejector-jets focusing on its flow properties was carried out by varying the geometric parameters. The area ratio of the primary nozzle, AR that was tested in the present measurement was 2.17 and 3.18, while the ratio of the length to the diameter of the duct downstream the primary nozzle inlet, L/D had values of 3.41, 6.82, and 10.23. For the frame work of flow characteristics, the wall pressures distribution of ejector-jet was investigated by experiment for basic study of ejector-jet performance. In result, terminal shock location and existence of series of oblique shocks are recognized. In this study, CFD analysis was conducted at the same time. And as a result of comparison experiment data with CFD analysis, the physical phenomena of ejector-jets were estimated.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.529-532
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• 2002

In coflow jets with relatively large size nozzle and low fuel jet velocity, the buoyancy effect arises from the density difference between fuel and air streams. The present study investigated the behavior of such a buoyant cold Jet both numerically and experimentally, especially when the fuel stream has higher density than air. It has been demonstrated that the cold jet has a circular cone shape since upwardly injected fuel jet decelerates and forms a stagnation region, when the fuel jet was composed of propane highly diluted with nitrogen. When the fuel was moderately diluted, numerical results showed the Kelvin-Helmholtz type instability along the mixing layer of the jet. The stagnation height increases nonlihearly with fuel jet velocity with the power of approximately 1.64.

• 한국분무공학회지
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• 제13권2호
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• pp.99-106
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• 2008

In this study, spray characteristics research of steady/pulsed injection in crossflow was performed experimentally in the model ramjet combustor. High-speed-camera photography was performed through a visualization window of model combustor, and then, steady and pulsed spray structures were observed and analyzed. Varying influx air temperature and fuel species, we could obtain the trajectory correlation in the steady injection case. In the experiment of pulsed injection, it is found that the pulsed frequency hardly influences spray trajectory. Also, it is found that, in the same injection pressure differential, the trajectory correlation of steady condition can be used for estimating pulsed spray trajectory.

• 한국가시화정보학회지
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• 제9권2호
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• pp.27-33
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• 2011

Supersonic liquid jet discharged from a nozzle has been investigated by using a ballistic range which is composed of high-pressure tube, pump tube, launch tube and liquid storage nozzle. High-speed Schlieren optical method was used to visualize the supersonic liquid jet flow field containing shock wave system, and spray droplet diameter was measured by the laser diffraction method. Experiment was performed with various types of nozzle to investigate the major characteristics of the supersonic liquid jet operating at the range of total pressure of 0.8 from 2.14 GPa. The results obtained shows that shock wave considerably affects the detailed atomization process of the liquid jet and as the nozzle diameter decreases, the shock wave angle and the averaged SMD of spray droplet tends to decrease.

• 한국추진공학회지
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• 제16권6호
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• pp.9-15
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• 2012

추력변화를 초공동 수중운동체의 추진체로 사용되는 수반응성 금속입자와 해수는 연소챔버 내에서 균질하게 혼합될 때 비추력이 극대화 된다. 본 연구의 목적은 상사성의 관점에서 분사기 형상이 입자 분포에 미치는 영향을 알아보는 것이다. 이를 위해 PIV기법을 이용하여 반경방향의 입자 분포와 입자 평균속도의 상사성에 대하여 알아보았다.

• 동력기계공학회지
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• 제4권1호
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• pp.33-38
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• 2000

The characteristics of center-driver jet pump which have multi-nozzle were studied in this research. Jet nozzles are connected outside of the bend rather than inserted in the bend in order to transport solid materials or fish without any harm. Jet pumps having one nozzle, two nozzles, four nozzles, and sixteen nozzles were tested in this study. The efficiencies and performances of jet pumps were studied for several nozzles shape, for three different mixing chamber shapes, for two suction area shapes. All the efficiency curves for these cases are presented in this paper.

• 한국원자력학회:학술대회논문집
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• 한국원자력학회 1998년도 춘계학술발표회논문집(1)
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• pp.541-546
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• 1998

증기 제트 응축에서 발생하는 응축하중을 실험적으로 고찰하였다. 네 가지 서로 다른 직경의 노즐 (5, 10, 15, 20mm) 과 증기분사기를 응축실험에 사용하였으며, 증기 질량유속과 물온도를 변화하면서 동압을 측정하였다. 실험결과에 의하면 압력파의 진폭은 노즐 직경이 작을수록 작았다. 한편 압력파의 진폭은 일반적으로 물온도가 증가할수록 증가하나 물온도가 어느 한도 이상으로 증가하면 오히려 감소하는 경향을 보였다. 그러나 물온도가 아주 높고 증기 질량유속이 큰 경우에는 불안정한 압력파가 발생할 가능성이 관찰되었다.

• 대한기계학회논문집
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• 제15권3호
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• pp.954-962
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• 1991

본 연구에서는 횡 방향으로 속도구배를 타내는 a=.part.W/.part.z에 대한 방정식을 3차원 운동량 방정식으로 부터 유도한 준 3차원 수학적 모델을 성정하여 해석하였다. 또한 수치 해석을 위하여 Chen에 의하여 고안된 유한 해석법과 2-방정식 저 레이놀즈 K-.epsilon. 난류모델, 그리고 Maeng에 의해 제시된 경계 공정 좌표계를 사용하였다. 그리 고 프로그램의 검증을 위하여 G.Ber geles가 수행한 실험치와 비교하여 그 타당성을 입증하였다.

• 대한기계학회논문집
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• 제16권2호
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• pp.302-312
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• 1992

Three dimensional velocity measurements of a 35.deg. inclined jet issuing into turbulent boundary layer on both concave and convex surfaces have been conducted. To investigate solely the effect of each curvature on the flow field, streamwise pressure variations are minimized by adjusting the shape of the opposite wall in the curved region. From the measured velocity components, streamwise mean vorticities are calculated to determine jet-crossflow interface. The results on convex surface show that the injected jet is separated from the wall and the bound vortex maintains its structure far downstream. On concave surface, the secondary flow in the jet cross-sections are enhanced and in some downstream region from the jet exit, the flow on the concave surface has been developed to Taylor-Gortler vortices