• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.148-151
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• 2007

We made two injectors that were equal to all design except for existence or nonexistence of swirl chamber of fuel part, because we want to find cooling characteristics at the injector face according to existence or non existence of swirl chamber of fuel part. And we set regenerative cooling channel in injector face for protecting injector face for prolonged combustion time. Two injectors were performed hot firing test, and then we compared cooling characteristics of two injectors. Also we compared O/F ratio effects on cooling characteristics and combustion characteristics.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.479-483
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• 2010

In this paper, a study for hybrid rocket combustion with cylindrical multi-port grain and swirl injector was performed to take advantage of regression rate. Change of the regression rate in the multi-port grain the placement of a swirl Injector experiments were performed. The results of multi-port grain using swirl injector were showed that the regression rate was increased compare with the shower head type injector.

• 유체기계공업학회:학술대회논문집
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• 1998.02a
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• pp.150-156
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• 1998

가스터어빈 트랜지션 덕트 내에서의 공기 역학적인 거동을 입구 스월각의 변화에 대하여 고찰하였다. 트렌지션 덕트가 작은 확산각(divergence angle)을 가지더라도 스트럿 영향으로 인한 탈설계점에서의 유동 패턴은 트랜지션 덕트 내에서의 유동특성을 더욱 악화시킨다. 시험범위의 스월각은 마하수 변화에 따라 손실계수에 큰 영향을 주지 못하였으며 트랜지션 덕트 내에서의 손실 정조는 만족할만 하나, 시험결과에 따르면 저압터빈의 노즐손실은 큰 입사각의 영향으로 커질것으로 생각되며, 또한 스트럿으로부터 떨어져 나오는 와류는 저압터빈의 로우터 블레이드의 진동에 악영향을 미칠 것으로 생각된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.9-9
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• 1999

각국의 공해 물질 배출량 규제가 엄격해지면서 저공해 가스터빈 엔진 개발의 필요성이 점점 대두되고 있다. 공해 물질 중 NOx는 고온에서 생성량이 급격히 증가하므로 배출량을 줄이기 위해서는 엔진 작동 온도를 낮추어야만 하고 이는 엔진 효율의 감소로 이어진다. 따라서 NOx를 줄이기 위해서는 작동 온도는 낮추지 않으면서 국부적인 고온 지역을 줄이고 연료가 고온 지역에 머무르는 시간을 감소하는 것이 가장 효과적이다. 이러한 방법으로 스월러를 장착하여 유입되는 공기에 스월을 주는 방법이 많이 연구되어 왔다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.66-71
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• 2005

In this study the regression rate of hybrid rocket fuel has been investigated by two methods. First method is to use swirl injectors for enhancement of regression rate. And second method is the modification of the helical grain deriving improvement of combustion area and generating swirl flow. Tests have been done with PMMA and gaseous oxygen. In this paper the incline angle of the helical grain was varied to find the optimal condition to obtain the max regression rate for a given operational condition.

• Journal of computational fluids engineering
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• v.6 no.1
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• pp.31-39
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• 2001

연소실 안으로 분출되는 스월 유동의 vortex breakdown mechanism에 대한 연구를 하였다. 3차원 유한 체적기법과 Runge-Kutta 시간 적분법이 적용되었으며, 난류모델은 dynamic large eddy simulation (DLES)이 적용되었다. 계산 시간의 효율성과 기억용량을 효과적으로 사용하기 위하여 message passing interface (MPI) 병렬계산 기법이 적용되었다. 스월 난류 유동에 있어서 vortex breakdown 거동을 가시적으로 표착 하였는데, 이는 스월 유동에 의한 난류 응력 증대, 난류 생성/소산율 증대 및 혼합율 증대에 대한 실험적 근거를 뒷받침하는 매우 중요한 결과이다. 또한 평균 속도와 난류 운동에너지에 대한 계산 결과도 실험 결과와 비교하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.251-255
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• 2005

By using liquid film thickness measurement the spray characteristics of swirl injector according to the geometric parameters were investigated in this paper. A specially designed injector having a variable backhole length, swirl chamber length, orifice length was used to measure the liquid film thickness. The spray characteristics of the injector were represented by mass flow rate according to the injection pressure, liquid film thickness in the lower orifice, spray cone angle.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.67-70
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• 2008

Production and dissipation of turbulent structure in a swirl stabilized combustor was investigated using three-dimensional Large Eddy Simulation analysis. The combustor of concern is the LM6000, lean premixed dry low-NOx annular combustor, developed by GEAE. Inlet condition was based on experimental data. Strong vortex breakdown in main stream, vortex ring proceeding downstream, and the turbulent structure periodically oscillating have been observed. Reasonable agreement was obtained by comparison of the results with experiments and previous LES studies.

• Journal of computational fluids engineering
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• v.11 no.2 s.33
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• pp.40-48
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• 2006

In the present, The theoretical and numerical results of gas flow characteristics inside a swirl injector are presented. For this purpose a one-dimensional (theoretical) model and 2D/3D CFD models are proposed for use in the design of the injector. It was found that contradictory to the classical theory about the compressible flow, the swirl has a significant effect on the mass flow rate and the choking conditions. It was found that the one-dimensional model provides reasonably accurate results compared with the 2D/3D numerical results, and thus can be used at the initial stage of the swirl-injector design process.

• 한국전산유체공학회:학술대회논문집
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• 2005.04a
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• pp.207-212
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• 2005

In this paper, we present the theoretical and numerical results of flow characteristics of a gas in a swirl injector. Proposed in this study are one-dimensional (theoretical) model and 2D/3D CFD models for use in the design of the injector. It was found that contrary to the classical theory about the compressible flow, the swirl gives a significant effect on the mass flow rate and the choking conditions. The one-dimensional model was found to Provide reasonably accurate results compared with the 2D/3D numerical results, so that it can be employed in th initial stage of the swirl-injector design process.