• Journal of Power System Engineering
• /
• v.14 no.2
• /
• pp.22-27
• /
• 2010

본 논문은 유한체적법에 근거한 CFD 분석기법을 이용하여 증기 이젝터의 성능에 대하여 구동노즐의 기하학적 형상에 따른 영향을 조사하였다. 구동노즐의 직경비를 변화시키고 또한 직경비를 일정하게하고 구동 노즐의 위치를 변화시키면서 최적의 조건을 조사하였다. 연구 결과 이젝터의 성능은 구동노즐의 직경과 노즐의 출구 위치에 의해 좌우됨을 확인하였다. 일정 노즐 면적비에 대하여 노즐 목 직경이 감소함에 따라 혼입율이 증가하는 것을 확인하였고 일정 노즐 목 직경에 대하여 면적비의 증가는 혼입율의 감소의 원인이 된다는 것을 확인할 수 있었다. 또한 혼입율은 노즐의 출구 위치에 따라 영향을 받는다는 것도 확인하였다. 혼입율은 노즐 출구의 위치가 이젝터의 상류로 이동할수록 증가하고 그 위치는 이젝터의 일정단면적부 직경(D)에 대하여 0.4D일 때 최적의 성능을 보였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2000.11a
• /
• pp.37-37
• /
• 2000

일반적으로 노즐 입구의 압력과 배압의 비가 어떤 임계값보다 큰 경우에 축소확대 노즐을 통하는 유동은 노즐목에서 초크하며, 노즐출구에서는 용이하게 초음속으로 된다. 노즐을 통하여 초음속으로 방출되는 제트유동에 관해서는 현재까지 많은 연구가 수행되었다. 이들 연구에 의하면 노즐 압력 비에 따라 노즐출구에서의 유동상태(즉 과팽창, 적정팽창, 부족팽창상태)가 결정되며, 노즐출구로부터 하류의 초음속 제트유동에서 발생하는 충격파 구조 및 위치, 제트경계의 구조 그리고 제트의 코어 등 유동의 기구가 비교적 상세하게 알려져 있다.(중략)

• Journal of Advanced Marine Engineering and Technology
• /
• v.36 no.8
• /
• pp.997-1002
• /
• 2012

Emission regulations have been strengthened step by step for marine engines. A noble measure is required both inside and outside of the combustion chamber. The combustion characteristics in cylinder have a very close relationship with the exhaust emission characteristics. Injection valve and nozzle hole geometry is an important factor for combustion. The study to improve the spray characteristics has concentrated on nozzle inlet geometry and nozzle hole diameter, but the exit geometry has not considered. In this study the nozzle exit angle variation was tested. The results show that the angle between $30^{\circ}$ and $60^{\circ}$ is more effective than the other cases.

• Proceeding of EDISON Challenge
• /
• 2013.04a
• /
• pp.327-330
• /
• 2013

Converging-diverging 노즐은 시스템 내부 유동에 적용되는 속도면적 법칙을 통해, 아음속 유동을 초음속으로 만드는 장치이며, 항공기 엔진 등에서 추력을 얻기 위해 쓰인다. 이상기체, 등 엔트로피를 가정한 동일 입구 조건에서, 출구로 빠져나오는 유동의 속도는 오직 면적 비에만 관계한다. 그러나 실제현상에서는, 출구에서의 유속이 유동의 압축성 효과 및 벽면에서의 전단력 등으로 인해 노즐 형상마다 상이한 결과를 낳는다. 본 연구에서는 EDISON Simulation을 활용하여 다양한 노즐 형상에 따른 출구에서의 Mach number를 구하고, 각각의 결과로부터 경향성을 찾는다. 또, 계산 결과를 이론식을 통해 도출되는 결과와 비교한다.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.38 no.3
• /
• pp.235-242
• /
• 2014

To investigate pressure distributions on the shaft surface of the air bearing, the commercial CFD software was employed to study three different nozzle geometries to improve the nozzle performance: general drill-shaped, matched cube-shaped and trimmed exit nozzles. Under the influence of stagnation point, the maximum pressure was observed at the center of shaft surface for all cases. Owing to the blocking effect of a fine gap between the shaft surface and the nozzle exit, the drill-shaped nozzle has the rapid local pressure increase near the nozzle exit corner, generating the ring vortex in the radial direction within pressure ratio of 6.92, and its pressure becomes negative in a certain range of downstream. In comparison, the contoured nozzle showed a local pressure increase in the measured range of pressure ratios, but a negative pressure appeared within the pressure ratio of about 10. The trimmed nozzle was seemed to extend the high pressure zone near the stagnation point in the radial direction substantially, and no negative pressure was appeared in the whole range. Based on these observations, it is found that trimming nozzle exit becomes more effective for improving the performance than modifying the nozzle inside contour.

• Journal of the Korean Institute of Gas
• /
• v.23 no.1
• /
• pp.12-18
• /
• 2019

Exhaust gas recirculation method is widely used among various methods for reducing nitrogen oxides in automobile engines and incinerators. In the present study, the computational fluid dynamic analysis was accomplished to derive the optimal location of air nozzle exit position by changing its position in a venturi tube for the maximum flue gas recirculation effect. In addition, the flue gas recirculation characteristics with a cone at the exit of air nozzle was elucidated with flue gas recirculation flow rate ratio and mixed gas exit temperature. When the air nozzle exit position was changed from the start position (z = 0) to the end position (z = 0.6m) of the exhaust gas recirculation exit pipe, the change of streamline and temperature distribution in the venturi tube was observed. The exhaust gas recirculation flow rate and the average temperature at the mixed gas exit position was quantitatively compared. From the present study, the optimal location of air nozzle exit position for the maximum flue gas recirculation flow rate ratio and maximum mixed gas exit temperature is z = 0.15m (1/4L). In addition, when the cone is installed at the outlet of the air nozzle, the velocity of the air nozzle outlet is increased, the flue gas recirculation flow rate was increased by about 2 times of the flow rate without cone, and the mixed gas exit temperature is increased by $116^{\circ}C$.

• Journal of the KSME
• /
• v.35 no.1
• /
• pp.36-45
• /
• 1995

주노즐내의 공기제트의 효율을 높이기 위해, 주노즐 제트 속도는 높을수록 높은 마찰력을 초래 하여 위사의 속도를 증가시킨다. 가속관의 길이가 증가하면 노즐출구에서의 공기의 속도와 난 류가 감소하며; 가속관의 직경이 증가할 때에는 공기속도가 감소하며 난류는 증가한다. 탱크압력, 가속관의 길이 등 유동조건에 따라 유동은 니들 끝과 가속관 출구에서 이중 초크(M=1)가 발 생할 수 있다. 에어가이드 직경과 노즐직경의 그 비율이 클수록 제트에 의한 유동의 비말동 반(entrainment)이 크게 된다. 실제 노즐직기내의 유동은 위사를 동반한 유동이므로 위와 같은 정성적인 설명에 위사의 물성치에 따른 고려를 반드시 하여야만 한다. 현장에서의 노즐설계는 노즐형상 자체의 영향은 물론 각종 위사의 물성치에 맞는 압축공기 압력 최적조건이 무엇인가를 찾는 일도 매우 중요하다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.5 no.4
• /
• pp.94-101
• /
• 2001

The shock structure of dual coaxial jet is experimentally investigated. Eight different kinds of coaxial, dual nozzles are employed to observe the major features of the near field shock structure on the supersonic, coaxial, dual jets. Four convergent-divergent supersonic nozzles having the Mach number 2.0 and 3.0 are used to compare the coaxial jet flows discharging from two sonic nozzles. The primary pressure ratio is changed in the range between 1.0 and 10.0, and the assistant jet ratio from 1.0 to 4.0. The results show that the impinging angle, nozzle geometry and pressure ratio significantly affect the near field shock structure, Mach disk location and Mach disk diameter.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2005.11a
• /
• pp.34-39
• /
• 2005

In this study, 3-D nozzle shape and the shape of nozzle at exit plane were adopted as design parameter of 3-D supersonic nozzle and numerical analyses for these parameters have been performed to investigate the flow and performance characteristics for design parameters of the turbine. Firstly, comparing results for nozzle shape, rectangular nozzle had less total pressure loss occurred in axial gap and more power by 1.5% than circular nozzle did. Next, comparing the results for the shape of nozzle at exit plane, it is found that the performance of partial admission turbine was largely depended upon the gap between nozzle wall at exit plane and the hub / tip of rotor blade and the length between nozzles.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.25 no.3
• /
• pp.1-13
• /
• 2021

Effects of the nozzle wall angles on the supersonic flow field in a thrust optimized nozzle were numerically investigated. The combustor and operating condition of 30-tonf rocket engine was selected to study the optimum nozzle shape. The nozzle flow of combustion products was realized by the shifting equilibrium calculation for the propellant of kerosene-LOx. The change of nozzle wall angles induced different developing patterns of the internal and secondary shock wave. The optimum nozzle was obtained when the internal shock was in a specific position at the nozzle outlet. The nozzle wall angles of the optimum nozzle were very similar to those of the optimum nozzle which does not consider the shock wave.