• Proceedings of the KAIS Fall Conference
• /
• 2002.05a
• /
• pp.155-159
• /
• 2002

This study is object to structural analysis of high-pressure injection nozzle. The finite element model was developed to compute the stress, strain for high-pressure injection nozzle. For structural analysis using result from FEM Code.

• Transactions of the Korean Society of Machine Tool Engineers
• /
• v.12 no.2
• /
• pp.37-43
• /
• 2003

This study makes to flow analysis of computational fluid dynamics(CFD) according to the basic theory of turbulent flow regarding high-pressure injection nozzle. It also makes structural analysis to find out the structural validity of the optimum shape of high-pressure injection nozzle. It divides to two areas such as plunger areas and high-pressure injection nozzle area including plunger.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.35 no.10
• /
• pp.1061-1066
• /
• 2011

In this study, the flow characteristics of an injection nozzle installed in a high-pressure holder for improving productivity were determined. The inlet velocity, nozzle inflow angle, and nozzle outlet diameter were selected as design factors having an influence on the flow characteristics, and numerical analysis was conducted for these factors. As the inlet velocity is high and the nozzle outlet diameter is small, the pressure and velocity of the injected flow are high. In the case of the nozzle inflow angle, the variation of flow characteristics according to angle was slight, but the highest pressure and velocity were found at $15^{\circ}$. In addition, the possibility of chip elimination by the injected flow was analyzed on the basis of the numerical results.

• Journal of the Korean Society of Manufacturing Technology Engineers
• /
• v.20 no.6
• /
• pp.793-798
• /
• 2011

In this study, it was grasped to the flow characteristics of cutting fluid injected by nozzle installed in high pressure holder for avoiding chip curling occurred during machining process. And for avoiding chip curling, the possibility of elimination under various chip conditions was checked. Consequently, the highest discharging pressure and velocity was shown in 150 of nozzle inflow angle. Also as nozzle outlet diameter is small, the pressure and velocity of injected flow are high. Moreover, It could be confirmed that width and thickness of chip have no direct effect on chip elimination and it is achieved by torque generated by injected cutting fluid.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.11 no.4
• /
• pp.59-66
• /
• 2007

In this paper, experimental investigation results of the effect of partial admission ratio on the performance of axial turbine was presented. A supersonic impulse turbine of gas generator cycle liquid rocket engine turbopump was used for the test. for experimental purpose, a nozzle block, in which total 14 number of axi-symmetric convergent-divergent nozzles are arranged circumferentially, was designed and manufactured. Partial admission ratio was controlled by changing the number of active nozzles. High pressure air was used as working medium for the test. The experimental result revealed that the performance of the supersonic impulse turbine does not much affected by the partial admission ratio for supersonic impulse turbine.

• Proceedings of the Korean Nuclear Society Conference
• /
• 2003.10a
• /
• pp.240.1-240.1
• /
• 2003

• Journal of the Korean Institute of Gas
• /
• v.8 no.1 s.22
• /
• pp.7-12
• /
• 2004

In the quality control of the aerosol skincare products containing powders, it is essential to guarantee that the contents in the bottle can be completely used without leakage or clogging of the nozzle. In this paper, the clogging caused by powder was investigated and the clogging can be effectively removed by emulsifying the contents containing powder with the LPG using a proper surfactant. And the spraying test shows that the contents in the bottle are completely propelled to outside by LPG when properly emulsified by POE(40) HCO.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.177-180
• /
• 2010

Two-stage light gas gun, sorted with Ballistic Range System, is used to research spray characteristics of supersonic liquid jets. When high pressure tube was pressurized to the 135 bar, diaphragm films which composed with OHP film are ruptured. Expansion gases accelerate a projectile approximately 250 m/s at the exit of pump tube. And accelerated projectile collides with liquid storage part and liquid jets were injected into supersonic conditions. Supersonic liquid jets show the multiple jets and generate shockwave at the forward region of jets. Supersonic liquid jets of speed and shockwave angle have different value at each case. Supersonic liquid jets with minimum velocities are injected with M=1.53 at the geometry condition of L/d=23.8.

• The Journal of the Korea Contents Association
• /
• v.10 no.10
• /
• pp.68-77
• /
• 2010

In the case of operating steam generators for long periods in nuclear power plants, sludge is accumulated inside the steam generator. This phenomenon could adversely affect the operation of the steam generator. This paper is about the design of a sludge washing apparatus which can remove the sludge efficiently and the control methods of the apparatus. In this paper, to design the sludge washing apparatus, firstly, we design nozzles for spraying high-pressure water through applying mathematical models and lab tests. Secondly, we establish the mathematical theory for performance parameters required to drive the sludge washing apparatus. Thirdly, we design physical structures of the apparatus based on the established performance parameters. Finally, we present the control methods of the apparatus. The sludge washing apparatus presented in this paper moves along the walls of the steam generator according to cracks in the tube array, and spray the high pressure water to remove the sludge. By this way, a relatively large amount of sludge formed in the inner surfaces can be washed very effectively.

• Aerospace Engineering and Technology
• /
• v.4 no.2
• /
• pp.135-141
• /
• 2005

The procedure of conceptual and detailed design of sub-scale combustor using bipropellant swirl or impinging injector with external or internal mixing for a liquid rocket engine are described in this paper. The sub-scale combustor uses liquid oxygen(LOx) and kerosene as propellants and has a injector head, an ablative material combustor wall and a water cooled nozzle. The injector head has LOx manifold, fuel manifold, fire face plate, one center swirl or impinging injector and 18 main swirl or impinging injectors.