• Transactions of the Korean Society of Automotive Engineers
• /
• v.19 no.2
• /
• pp.117-124
• /
• 2011

Valve springs with non-circular cross-section are widely used in automotive engines. Because of the reduced height, the oval cross-section provides some merits in its install height and stress distribution. This paper introduces a new method to generate optimal shape of the non-circular cross-section. For given width and height, arbitrary shape of the cross-section are described using the Hermite spline curves. Cross-section area and maximum stress level are chosen as performance indices, and nonlinear optimization problems are formulated with inequality constraints. Compared to a production spring wire, cross-section area can be reduced about 2.4 [%] without increasing maximum stress level. In addition, the other approach gives an optimum cross-section which reduces maximum stress level of 2.0 [%] without increasing cross-section area.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.25 no.1
• /
• pp.19-28
• /
• 2021

In rotating detonation engine(RDE), only the detonation wave is moving around the outer wall of the combustor. Neither a mechanical part nor flow is rotating in RDE. Thus, the RDE cross section is not necessary to be circular, but arbitrary closed section is possible. A RDE of tri-arc cross section is designed and As an example of an arbitrary cross sectioned RDE, a RDE of tri-arc cross section is designed in this study, and operational and performance characteristics were examined experimentally. The rotation of the detonation wave is confirmed by dynamic pressure sensor and high-speed camera, while the characteristics of the detonation wave were investigated at the concave and convex surfaces. In the present study, the thrust level of 17.0 N to 96.0 N was obtained depending on the mass flow rate.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2004.10a
• /
• pp.27-35
• /
• 2004

In this paper a method for finding solution of acoustic, vortex and entropy wave-equations in a cylindrical tube with variable section area was suggested under the consideration of that the high frequency instability in a rocket engine combustion chamber is an acoustic phenomena, which is coupled with combustion reaction, and that a combustion chamber and exhaust nozzle are usually shaped cylindrically. As a consequence of that some method, which enable the quantitative analysis of the influence of entropy and vortex waves to acoustic wave, was suggested.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.11a
• /
• pp.393-396
• /
• 2006

This paper presents the characteristics of the performance parameters of dual mode(ramjet-scramjet combined) engine, inlet and combustor for wide range of flight Mach number, resulted from the analysis of its operating limitations. The transitional-critical flight Mach number from ramjet to scramjet and the performance of two types of combustors, such as constant pressure- and constant area- combustor, are conceptually evaluated.

• Proceedings of the Korea Water Resources Association Conference
• /
• 2017.05a
• /
• pp.221-221
• /
• 2017

본 연구에서는 국내는 물론 전 세계적으로 널리 사용되고 있는 SWAT 모형을 대상으로 하천 단면 관련 입력변수가 유량 및 수질 모의에 미치는 영향을 분석하였다. 본 연구에서는 남한강 상류 충주댐 유역을 연구대상지역으로 연구를 진행하였으며, 충주댐 유역 내 소유역 중에서 국립환경과학원에서 국내 하천을 대상으로 구축한 한국형 Reach File(KRF) 내 실측 하천단면 정보가 존재하는 소유역에 대하여 실측 하천단면 정보를 적용하였다. 또한 본 연구를 위해 사용자가 구축한 소유역별 하천단면 정보 입력 자료를 통해 수문 및 수질 모의가 가능하도록 기존 SWAT 모형의 엔진 소스코드를 개선하였다. 유역 최종 유출구와 KRF의 실측 하천단면 정보를 적용한 소유역의 유량과 수질(유사량)에 대해서 실측 하천단면 정보 적용 전과 후의 모의 결과를 비교한 결과 유역 최종 유출구에서는 유량 및 유사량 모두 큰 변화는 나타나지 않았다. 이는 전체 유역 중 실제 하천단면 정보를 적용한 소유역의 비중이 작기 때문으로 판단되었다. 하지만 하천단면 정보를 적용한 소유역에서는 유량 및 유사량 모두 적용 전/후 차이가 나타났다. 특히 저유량 부분에서의 유사량이 큰 변화를 나타냈다. 하지만 본 연구에서 실측 하천단면 정보를 적용한 소유역은 유량 및 수질관측소가 위치하지 않는 미계측 유역으로써 실제 유량 및 수질 모의 정확도 향상 여부에 대한 평가가 불가능하였다. 따라서 향후 유량 또는 수질 관측이 이뤄지고 있는 계측 유역을 대상으로 실제 모형 모의 정확도 향상 여부에 대한 분석이 필요할 것으로 판단된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.10a
• /
• pp.78-82
• /
• 2003

The cooling mechanism for a regenerative cooling liquid rocket engine of 10tf-thrust using kerosene as a fuel was studied from the viewpoint of curtain cooling. Based on the concept of a highly-stratified gas flow in the combustion chamber, the cross section of the combustion chamber was spilt into 2 independent parts, core and exterior part. Additional fuel is injected into the exterior section and gas temperature can be reduced in the exterior section. Consequently, the heat flux into the coolant and wall temperature are reduced and the thermal stability of a liquid rocket engine could be improved.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.10
• /
• pp.66-72
• /
• 2003

The cooling mechanism for a liquid rocket engine of 10tf-thrust using kerosene as a fuel was studied from the viewpoint of both the regenerative and curtain cooling. Based on the concept of a highly-stratified gas flow in the combustion chamber, the cross section of the combustion chamber was spilt into 2 independent parts, core and exterior part. Additional fuel is injected into the exterior section and gas temperature can be reduced in the exterior section. Consequently, the heat flux into the coolant and wall temperature are reduced and the thermal stability of a liquid rocket en g i.ne could be improved.

• Transactions of the Korean Society of Automotive Engineers
• /
• v.5 no.3
• /
• pp.147-158
• /
• 1997

This paper presents the analysis technique and procedure of main engine components-cylinder block, cylinder liners, gasket and cylinder head-using the finite element method, which aims to assess mainly the potential of lower oil consumption in a view point of engine design and to decide subsequently the accuracy of engine design which was done. The F.E. model of an engine section consisting of one whole cylinder and two adjacent half cylinders is used, whereby the crankcase is cut off at the block bottom deck. By means of a 3-dimensional F.E. model-including cylinder block, liners, gasket, cylinder head, bolts and valve seat rings as separate parts a linear analysis of deformations and stresses was performed for three different loading conditions;assembly, thermal and gas loads. For the analysis of thermal boundary conditions also the temperature field had to be evaluated in a subsequent step.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.8 no.4
• /
• pp.55-66
• /
• 2004

In this paper a method for finding solutions of acoustic, vortex and entropy wave equations in a cylindrical tube with variable section area was suggested under the consideration of that the high frequency instability in a rocket engine combustion chamber is an acoustic phenomena, which Is coupled with combustion reaction. and that a combustion chamber and exhaust nozzle are usually shaped cylindrically As a consequence of that some method. which enable the mathematical analysis of the influence of entropy and vortex waves to acoustic wave. was suggested. According to the method reflection coefficients of acoustic wave on a supercritical nozzle was numerically calculated, through which it was presented that entropy or vortex waves can strengthen or weaken the reflection rate of acoustic wave.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.643-646
• /
• 2017

In a liquid rocket engine using hydrocarbon fuels, cooling of the combustion chamber wall is necessary to prevent the combustion chamber wall from melting or structurally deforming due to high heat flux. Among the various methods, regenerative cooling, which uses fuel as a coolant and then injects it into the combustion process, has good performance. This study investigated the heat transfer characteristics of kerosene as a coolant by varying the copper cross-sectional area, the flow rate in the channel, and the current applied to the channel. Convective heat transfer occurred rapidly when the cross-sectional area of the copper channel was small and when the kerosene flow velocity was fast.