• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 춘계학술대회
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• pp.2029-2034
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• 2004

Spiral jet is characterized by a wide region of the free vortex flow with a steep axial velocity gradient, while swirl jet is largely governed by the forced vortex flow and has a very low axial velocity at the jet axis. However, detailed generation mechanism of spiral flow components is not well understood, although the spiral jet is extensively applied in a variety of industrial field. In general, it is known that spiral jet is generated by the radial flow injection through an annular slit which is installed at the inlet of a conical convergent nozzle. The present study describes a computational work to investigate the effects of annular slit on the spiral jet. In the present computation, a finite volume scheme is used to solve three dimensional Naver-Stokes equations with RNG ${\kappa}-{\varepsilon}$ turbulent model. The annular slit width and the pressure ratio of the spiral jet are varied to obtain different spiral flows inside the conical convergent nozzle. The present computational results are compared with the previous experimental data. The results obtained obviously show that the annular slit width and the pressure ratio of the spiral jet strongly influence the characteristics of the spiral jets, such as tangential and axial velocities.

• 한국소음진동공학회논문집
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• 제14권1호
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• pp.50-55
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• 2004

In this study, slit-tones by plane impinging jet are investigated experimentally over the whole subsonic flow range, especially at low speeds, in order to obtain the instability behaviour of impinging plane jet. Slit-tones are generated at low speeds associated with laminar shear layer instability as well as at high speeds associated with turbulent instability. Most of low-speed slit-tones are induced by symmetric mode instability unless the slit is not so wide, in which case antisymmetric modes are induced like edge-tones. It is found that the frequencies at low speeds ate controled by the unstable condition of the vortex at the nozzle exit and its pairings by which the frequencies are decreased by half. In the case of symmetric modes related with low-speed slit-tones, frequencies lower than those associated with one-step pairings are not found.

• Journal of the Korean Society for Industrial and Applied Mathematics
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• 제13권4호
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• pp.237-245
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• 2009

A numerical solution is provided for a jet produced by a flow emerging from a slit at the bottom corner of a quarter plane. The flow is characterized by the Froude number F, based on the net volume flux and the width of the slit. We perform the free-surface flow for various values of F and another parameter corresponding to the position of the vertical wall. A jet with back-flow near the edge of the vertical wall is obtained, and the limiting case is a jet with a stagnation point.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.502-507
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• 2003

Spiral jet is characterized by a wide region of the free vortex flow with a steep axial velocity gradient, while swirl jet is largely governed by the forced vortex flow and has a very low axial velocity at the jet axis. However, detailed generation mechanism of spiral flow components is not well understood, although the spiral jet is extensively applied in a variety of industrial field. In general, it is known that spiral jet is generated by the radial flow injection through an annular slit which is installed at the inlet of convergent nozzle. The objective of the present study is to understand the flow characteristics of the spiral jet, using a computational method. A finite volume scheme is used to solve 3-dimensional Navier-Stokes equations with RNG ${\kappa}-{\varepsilon}$ turbulent model. The computational results are validated by the previous experimental data. It is found that the spiral jet is generated by coanda effect at the inlet of the convergent nozzle and its fundamental features are dependent the pressure ratio of the radial flow through the annular slit and the coanda wall curvature.

• 한국해양공학회지
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• 제35권1호
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• pp.24-37
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• 2021

As one of the development directions of high-performance ships to reduce greenhouse gas emissions, there is research on high-performance propellers. However, in the case of conventional screw propellers, as they have been studied for a long time, there is a limit to improving efficiency only by depending on the conventional design and analysis methods. In this study, we tried to solve the problems using the Coanda effect by spraying a jet on the surface of the hydrofoil. The Coanda hydrofoil consists of a tunnel and jet slit to make jet flow. The computation was performed for each tunnel and slit position, and the efficiency according to the geometry of the hydrofoil was analyzed. In addition, a study on the 3D geometry change was conducted to analyze the performance according to the span direction spraying range and hydrofoil shape. As the height of the slit and the diameter of the tip were lower, when the slit is located in the center of the hydrofoil, the lift force increased and the drag force decreased. The increase rate of lift-to-drag ratio was different according to the shape of the hydrofoil, and the efficiency of the spraying condition of 0.1S-0.5S, which had the least effect on the vortex at the tip of the blade, was high for all 3D hydrofoils. When the geometry of the slit was optimized, and also the shape and spray range of the hydrofoil in 3D was considered, the efficiency of the jet sprayed hydrofoil was increased.

• 한국추진공학회지
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• 제26권1호
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• pp.60-67
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• 2022

본 연구는 정상초음파 가진 유무에 따른 초음파 무화 케로신 화염의 거동변이를 분석하기 위해 수행되었다. Slit-jet 노즐을 통과하며 생성된 연소영역은 DSLR, ICCD 및 초고속카메라와 슐리렌 기법을 통해 가시화되었고, 연료소모량은 정밀저울을 통해 측정하였다. 그 결과, 정상초음파 가진시, OH 라디칼의 강도가 증가하는 것이 관찰되었고 정상파장 상단부에서 최적 연소 조건이 형성됨을 확인하였다.

• 한국추진공학회지
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• 제21권1호
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• pp.17-25
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• 2017

초음파 진동자에 의해 미립화된 탄화수소계 액체연료를 태우는 버너의 연소특성을 고찰하기 위한 실험이 수행되었다. 고속카메라와 열화상 카메라를 이용하여 slit-jet 버너에서 생성된 화염의 이미지를 획득하였으며, 후처리를 통해 화염의 형상과 온도구배를 면밀히 분석하였다. 또한, 정밀유량 계측법을 이용하여 수송기체 실험조건 변화에 따른 연료소모량을 측정하였다. 그 결과, 수송기체 유량이 증가하면 무화된 연료의 분사량도 같이 증가한다는 사실을 확인하였으나, 낮은 유량 조건에서는 주변 장치의 진동에 의해 공연비(air/fuel ratio)와 수송기체 유량의 상관성이 관찰되지 않았다. 또한, 수송기체 유량과 초음파진동자의 소비전력이 증가하면 연소반응이 촉진되어 연소영역이 신장되고 화염온도가 증가하였다.

• 한국추진공학회지
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• 제22권6호
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• pp.1-10
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• 2018

초음파 진동자에 의해 미립화된 탄화수소계 액체연료를 분사하는 버너에서 생성되는 화염의 거동을 고찰하기 위한 실험이 수행되었다. 고속카메라와 열화상 카메라를 이용하여 slit-jet 버너에서 생성된 화염과 연소장 이미지를 획득하였으며, 후처리 과정을 통해 화염과 연소장의 구조변이를 면밀히 분석하였다. 그 결과, 수송기체 유량이 증가하면 연소반응이 촉진되어 연소반응영역이 신장되고, 반응온도가 증가하였다. 또한, 시간 변화에 따른 가시화염과 IR 연소장의 거동변화 비교를 통해 화염의 진동원인을 고찰하였으며, 화염면적의 FFT분석을 통해 생성화염의 진동주파수도 확인하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2010년 춘계학술대회논문집
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• pp.448-450
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• 2010

Free surface liquid jet impingement, which is applicable to cooling of hot plates in a steel-making process, is investigated numerically by solving the conservation equations of mass, momentum and energy in the liquid and gas phases. The free-surface of liquid-gas interface is tracked by an improved level-set method incorporating a sharp-interface technique for accurate imposition of stress and heat flux conditions on the liquid-gas interface. The level-set approach is combined with a non-equilibrium $k-{\omega}$ turbulence model. The computations are made for slit nozzle jets to investigate their flow and cooling characteristics. Also, the effects of jetting angle, velocity and moving velocity of plate on the interfacial motion and the associated flow and temperature fields are quantified.

• 한국가시화정보학회지
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• 제7권2호
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• pp.28-34
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• 2010

Two turbulent jet with different sinusoidal nozzle exit configurations of in-phase and $180^{\circ}$ out-of-phase were investigated experimentally using a smoke-wire method and a hot-wire anemometry. Mean velocity and turbulence intensity were measured at several downstream locations under $Re_D\;=\;5000$. For the case of in-phase nozzle configuration, the length of potential core exhibits negligible difference with respect to the transverse locations (0, $\lambda/4$ and $\lambda/2$), similar to that of a plane jet. On the other hand, a maximum difference of 30% in the potential-core length occurs for the $180^{\circ}$ out-of-phase configuration. The spatial distributions of turbulence intensities also show significant difference for the nozzle of $180^{\circ}$ out-of-phase, whereas non-symmetric distribution is observed in the near-exit region(x/D = 1) for the in-phase sinusoidal nozzle jet. Compared to a slit planc jet, the sinusoidal nozzle jets seem to suppress the velocity deficit as the flow goes downstream. The sinusoidal nozzle jet was found to decrease turbulent intensity dramatically. The flow visualization results show that the flow characteristics of the sinusoidal nozzle jet are quite different from those of the slit plane jet.