• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.6
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• pp.61-68
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• 2020

7-tonf turbopump real-propellant tests in Naro Space Center were conducted and high-frequency signals from an accelerometer and pressure sensors installed on the casing and the inlet/outlet pipeline of LOX pump were analyzed to estimate the structural and hydrodynamic stabilities. Waterfalls, frequency spectrums and RMS(Root Mean Square) values of the measured signals were calculated and characteristic instability frequencies by the rotating cavitation and the rear floating ring seal(F.R.S) were investigated. Static pressures of the inlet/outlet pipeline and an acceleration of the pump casing are strongly affected on pressure fluctuation induced by the rear floating ring seal in the leakage path. Despite the acceleration RMS value seems totally small, the rotating-speed-related synchronous frequency affecting the shaft instability is distinctly observed in the frequency contour.

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.143-149
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• 2005

To evaluate the hydraulic and cavitation performance of a fuel pump for a liquid rocket engine, performance tests of the pump, which consist of hydraulic tests and cavitation tests, were conducted in water environment with various condition. In the hydraulic tests, the head, efficiency and volute pressure distribution of the pump are found to follow the conventional similarity rule, whereas the secondary flow pressure shows a small deviation from the similarity rule. As the floating gap is constricted, the efficiency of the pump improves and the secondary flow pressure decreases. However, the inner diameter of bypass line orifice does not show clear relationship with the pump efficiency. In the cavitation tests, measurements of the head and the NPSH indicate that the pump shows better cavitation performance as the rotational speed of the pump increases.

• Proceedings of the KAIS Fall Conference
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• 2010.11b
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• pp.824-827
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• 2010

본 논문은 전동형 모터의 Rotor의 자동 성형을 위한 자동화된 주조기 개발에 대한 결과이다. 개발된 자동화된 Rotor 전용 주조기는 수평형에 비해 금형의 크기가 약 1/2정도 이므로 금형 체결력이 반감되고, 기계 구조는 매우 작아진다. 그리고 Al용탕이 사출되는 과정에서 Spool -> Runner -> Gate -> Cavity(제품)에 이르기까지의 Runner를 최소화하여 재용융을 위한 에너지의 비용 절감을 할 수가 있다. 금형 구조가 간단하므로 금형비가 저렴하여 다품종 소량생산에 매우 유리하다. 개발제품은 수직형 구조로 알루미늄 용탕의 윗면의 공기가 금형의 유로 상측에 위치하므로 공기(gas)가 먼저 배출되어 사출(주조)후 Rotor 성형부에 남아 있는 기포가 최소화된다. 그러므로 충진도가 높아진다. Rotor 코아(규소강)가 크더라도 수직형은 금형내에 삽입(Inset)하기가 쉽고 또한, 제품의 착탈 부위와 사출부위가 다르기 때문에 작업성, 안전성이 우수하고 생산성이 매우 높다. 수직형은 충진 밀도가 매우 높고 밀도가 균일하기 때문 Rotor의 회전 소음, 진동에 대한 품질이 매우 우수하다. 따라서 고효율, 고품질의 전동모터 Rotor 제품 생산에 매우 효과적인 장비라 할 수 있다.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.4
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• pp.10-18
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• 2007

A tested micro axial-type turbine consists of two stages and its mean radius of rotor flow passage is 8.4 mm. This turbine could be applied to a driver of micro power system, and its rotational speed in the unloaded state reaches to 100,000 RPM. The performance of this system is sensitive depending on the blade angles of the rotor and stator because it is operated in a low partial admission rate, so a performance test is conducted through measuring the specific output power and the net specific output torque with various blade angles on the nozzle, stator and rotor. The experimental results show that the net specific output torque is varied by 15% by changing the rotor blade angle, and the optimal incidence angle is about $10.3^{\circ}$.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.1
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• pp.76-81
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• 2016

At negative-g condition, a float-type valve can open the passage of fuel in order to it flows continuously through a pressurized fuel tank system. Since specialized test conditions and high-cost supports are required, it is truly difficult to test the valve in a real high-speed test. Therefore, this paper contains performance analysis of a float-type fuel supply valve through flight tests conducting roll and negative-g maneuvers.

• Journal of the Korean Society for Precision Engineering
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• v.20 no.8
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• pp.54-61
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• 2003

The first stage rotating blade of industrial gas turbine is one of the components that is normally run in exposed state at the highest temperature of the combustion gas stream. For this reason superior materials and advanced cooling technology are required to allow higher heat resisting characteristics of the component. The 1st stage blade of a selected commercial gas turbine blade made of directionally solidified Ni-based superalloy has a row of cooling holes on its trailing edge. In most cases, minor cracks have been found at some of the root cooling holes after one cycle operation (24,000 hrs) or even shorter operation time because of the high temperature gradient and the frequently alternating thermal stress. In the repair process, unfortunately, it is usually very difficult to get rid of the damage due to the fact that cracks are initiated at the root cooling hole and propagated deep into the hole. In this study, the feasibility of removing the sidewall cracks in the hole by utilizing EDM drilling has been investigated. Also the criteria of surface integrity for EDM drilling were established to achieve high quality repair as well as machining accuracy.

• KOMUNHWA
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• no.57
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• pp.195-210
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• 2001

One kiln site of Koryo Earthenware in Hwakok-ri, Ansung was excavated from March 15, 1999 to May 15, 1999 by Museum Team of Ehwa Women's University, and also other one earthenware kiln site was confirmed as exposed figure on the ground. In this study, the

• Transactions of the Korean Society of Mechanical Engineers B
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• v.35 no.8
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• pp.781-787
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• 2011

We design a four-stage propane-refrigerant centrifugal compressor for an LNG plant. Using a commercial code, we aerodynamically designed the compressor at each design point of the corresponding stages. We estimated the one-dimensional aerodynamic design output and the three-dimensional shape of the impeller flow passage via three-dimensional flow analysis. In particular, we discuss in detail the flow characteristics of the impeller and the vaneless diffuser passages of the fourth-stage compressor in terms of the velocity fields, the pressure, and the entropy distributions of the flow passages. We include the flow effects of the tip clearance flow, because at this stage the rotating speed and total inlet pressure are higher than those at the other compressor stages are. We carried out performance tests of the designed compressor stages using propane as a refrigerant in the LNG cycle. The practical evaluation could lead to design enhancements in the future.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.22 no.6
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• pp.460-468
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• 2021

This study investigated the enhanced combustion efficiency of an "air-cooled combustion system" with single F.D. fan, and performed a numerical analysis for the operation and design conditions to increase the combustion efficiency. The combustion efficiency in an actual combustor was compared before and after the structure modification. Numerical analysis for application of a single fan revealed the difficulty of forming a turbulence for circular combustion conditions. This is because the supply ratio of combustion air supplied into 2 flow paths becomes irregular in the combustion furnace due to a change in friction force and pressure in each flow path. Subsequently, two methods of supplying air into the combustion furnace were analyzed numerically to obtain the optimal combustion conditions of an air-cooled combustion system. The first method involved injecting the preheated combustion air after a 180~360 degree rotation from the outer wall, whereas in the second method, the combustion air was injected into the combustion furnace in a tangential direction after primary heat exchange outside the combustion furnace, by applying a rotatable vane structure in the combustion furnace. Results reveal that application of a single F.D. fan to the air injection into a rotatable combustion furnace is desirable for optimization of the combustion conditions for applying a duct structure having a dual cooling wall for the cooling of the outer wall of the combustion furnace, and for maintaining perfect mixing in the combustion furnace. We therefore confirmed enhanced combustion efficiency by comparing the actual combustion efficiency before and after structure modification.

• Journal of the Korean Society of Marine Environment & Safety
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• v.15 no.3
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• pp.251-256
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• 2009

In this research, we experimentally studied flow characteristic by applying PIV measuring techniques which could measure the point velocity of all flow field and measuring the unsteady velocity of surrounding disk generated in a short time. Time range of great velocity change following quick closing of the slide valve was within 0.1s and the cycle was presumed to be 0.12s as a result of comparison study between the result of point flow field and of existing pressure change. Also, surrounding disk flow inside the circular pipe was closed from the upper part and flow road was getting narrow and advanced to the lower part incidentally quickly there was a tendency that the size of the flow back velocity to the upper part immeadiately after the closure decreased to 4/120s and increased again. There was flow back velocity component in y/D=0.2 lower part by the influence of flow back to the upper part after complete closure and the vortex flow of 0.2D-size near y/D=0.7, x/D=-0.3 was observed.