• 정보보호학회논문지
• /
• 제34권3호
• /
• pp.379-392
• /
• 2024

데이터의 급속한 증가와 함께 저장 공간 절약과 데이터 전송의 효율성이 중요한 문제로 대두되면서, 데이터 압축기술의 효율성 연구가 중요해졌다. 무손실 알고리즘은 원본 데이터를 정확히 복원할 수 있지만, 압축 비율이 제한적이며, 손실 알고리즘은 높은 압축률을 제공하지만 데이터의 일부 손실을 수반한다. 이에 딥러닝 기반 압축 알고리즘, 특히 오토인코더 모델이 데이터 압축 분야에서 활발한 연구가 진행됐다. 본 연구에서는 오토인코더를 활용한 새로운 부채널 분석 데이터 압축기를 제안한다. 제안하는 부채널 데이터 대상 압축기는 부채널데이터 특성을 잘 유지할 뿐만 아니라, 기존의 널리 사용되는 Delfate 압축방식 대비 높은 압축률을 보인다. 로컬 연결 레이어를 사용한 인코더는 부채널 데이터의 시점별 특성을 효과적으로 보존하고, 디코더는 멀티 레이어 퍼셉트론을 사용하여 빠른 압축해제 시간을 유지한다. 상관 전력 분석을 통해 제안된 압축기가 부채널 데이터의 특성을 손실 없이 데이터 압축이 가능을 증명하였다.

• 한국가스학회지
• /
• 제22권5호
• /
• pp.24-30
• /
• 2018

극한지 장거리 천연가스 배관망의 경우 배관 특성 및 노선 조건에 따라 가스압력이 감소되기 때문에 가스 압력유지를 위한 승압 설비가 필요하다. 적절한 가스 압력 유지를 위해 승압기지 위치 간격을 근거리로 하여 압축비를 줄이거나 장거리로 하여 압축비를 증가시킬 경우 승압기지의 주요설비 가격, 건설 및 운전비용 등이 고려된 경제성 확보가 필요하다. 따라서 본 연구에서는 극한지 장거리 배관망 건설에 대한 선행 연구조사를 검토하고 극한지 지역에서 승압기지의 건설비용을 절감할 수 있는 주요설비를 구성하여 공정 개념설계를 수행하였다. 특히 러시아의 야쿠츠크~알단지역에 대한 가상 지역을 선정하였고, 이 가상지역은 총 배관길이 533km 이며, 승압기지 건설 위치를 달리한 시나리오를 제시하고 승압기지의 주요설비에 대한 용량을 산정하였다. 이 결과를 바탕으로 승압기지 건설비용을 최소화할 수 있는 경제성 평가 방안을 검토하였다.

• 대한기계학회논문집B
• /
• 제35권8호
• /
• pp.781-787
• /
• 2011

본 연구에서는 4단으로 구성된 LNG 플랜트용 프로판 냉매 원심 압축기 각 단의 설계점에 대해 상용 코드를 이용하여 공력설계를 하였다. 1차원 공력 설계 결과와 3차원 유로 형상의 타당성은 유동해석을 통해 확인하였다. 특히 입구전압이 높고 회전수가 큰 4단 압축기 임펠러의 유로와 베인리스 디퓨저 내부 유동에 대한 속도장, 압력장 및 엔트로피 등의 유동특성에 대해 고찰하였고, 아울러 익단 간극이 유동장에 미치는 영향에 대해서도 알아보았다. 본 연구 결과는 프로판 냉매 압축기의 시스템 제작에 활용될 것이며 추후 실제 실험결과와 비교하고자 한다. 향후 설계된 프로판 냉매압축기에 대한 LNG 플랜트에서의 실증시험을 통해 구체적인 설계결과에 대한 평가 및 설계 개선이 이루어지리라 생각한다.

• Journal of Advanced Marine Engineering and Technology
• /
• 제34권5호
• /
• pp.695-702
• /
• 2010

Numerical analysis information will be very useful to improve fluid system. General information about an internal gas flow is presented by numerical analysis approach. Relating with hydrogen compressing system, which have an important role in hydrogen energy utilization, this should be a useful tool to observe the flow quickly and clearly. Flow characteristic analysis, including pressure and turbulence kinetic energy distribution of hydrogen gas coming to the cylinder of a reciprocating compressor are presented in this paper. Suction-passage model is designed based on real model of hydrogen compressor. Pressure boundary conditions are applied considering the real condition of operating system. The result shows pressure and turbulence kinetic energy are not distributed uniformly along the passage of the Hydrogen system. Path line or particles tracks help to demonstrate flow characteristics inside the passage. The existence of vortices and flow direction can be precisely predicted. Based on this result, the design improvement, such as reducing the varying flow parameters and flow reorientation should be done. Consequently, development of the better hydrogen compressing system will be achieved.

• 한국신재생에너지학회:학술대회논문집
• /
• 한국신재생에너지학회 2009년도 춘계학술대회 논문집
• /
• pp.422-425
• /
• 2009

A sea water source cascade heat pump was designed and tested in this study. The system was designed to perform a single stage operation in summer, as well as a cascade operation in winter to ensure the high temperature lift. A steady-state simulation model was developed to analyze and optimize its performance. The simulation results show that the R717 exhibits best performance among combinations considered in this study. A R410A also exhibits the highest performance among HFCs with the smallest compressor displacement. A 15-RT R410A-R134a pilot system was installed in the 5-story commercial building at Samcheok City by the East Sea. A scroll type R410A compressor, a reciprocating type R134a compressor, plate type condenser/evaporator/ cascade heat exchanger and two electronic expansion valves were used to build a pilot. A titanium plate type heat exchanger is also used for the heat exchanging with a sea water. The heat source/sink water is supplied from the well below the seashore in the depth of 5 m. In the initial test of the system, supply water temperature was rising up to $67^{\circ}C$ using a sea water heat source of $9^{\circ}C$, while an ambient temperature was $4.5^{\circ}C$.

• Tribology and Lubricants
• /
• 제27권2호
• /
• pp.88-94
• /
• 2011

The tribological characteristics of the swash plate surface of a compressor which is for automobile were investigated. For surface treatments, PTFE and $MoS_2$ are used as a solid lubricant, together with copper alloy. Test condition is set considering actual driving condition. Wear testing is conducted using pin on disk type tester, and the coefficient of friction and the temperature on friction surface are measured. Also, to determine the wear patterns, cross-section of friction surface is analyzed by SEM(scanning electrode microscope). The $MoS_2$, both at dry and lubricated conditions, friction surface and the coefficient of friction maintained rather stable results. But, the PTFE, at oil less condition, sample resulted in rather unstable condition. In case of copper alloy, quite higher friction coefficients(higher than 0.1) were obtained at dry condition. At the temperature of $125^{\circ}C$, seizure has occurred.

• 한국유체기계학회 논문집
• /
• 제19권5호
• /
• pp.5-11
• /
• 2016

The purpose of this study is to design the transonic centrifugal compressor impeller with splitter blades and analyze the flow fields with respect to various splitter blades. Seven impellers with different splitter chord length or pitchwise location were tested by using CFD method. To investigate aerodynamic performance, Mach number distribution and entropy distribution were confirmed. As a result, it is found that the size of transonic region and shock wave location are related to the splitter chord length and pitchwise location. Also the impeller with long chord length of splitter shows higher total pressure ratio but lower efficiency than those of the impeller with short chord length of splitter. In terms of pitchwise location, the impeller with the splitter located in mid-pitch of main blades shows the best performance with respect to pressure ratio and efficiency.

• Journal of Advanced Marine Engineering and Technology
• /
• 제33권7호
• /
• pp.1034-1043
• /
• 2009

Hydrogen energy is becoming popular day by day due to its renewability and pollutaaant free natures. Hydrogen gas pressure which is after passing through reciprocating compressor part has high pulsation wave form. A unit, snubber is used as compressor components to reduce the harmful pulsation waveform and to remove the impurities in the hydrogen gas. An experiment has been conducted to investigate the pulsation reduction performance of different arrangement of snubber i.e. snubber array used in reciprocating compression system. Analyzing the snubber array experimental data, it is found that the pressure fluctuations are reduced from 90.1977% ~ 92.6336% with pressure loss 1.5013% ~ 4.9034% for compressor operation at different speed which ensure the good performance of snubber-array as pulsation damper in hydrogen compressing system.

• 대한설비공학회:학술대회논문집
• /
• 대한설비공학회 2009년도 하계학술발표대회 논문집
• /
• pp.1513-1520
• /
• 2009

Renewability and pollutant free energy source makes hydrogen energy popular rapidly. Hydrogen gas pressure which is after passing through reciprocating compressor part has high pulsation wave form. A unit, snubber is used as compressor components to reduce the harmful pulsation waveform and to remove the impurities in the hydrogen gas. An experiment has been conducted to investigate the pulsation reduction performance of a steel pipe used in snubber system. The amplitude of pressure reduction were varied from $0.054{\sim}0.321\;kPa$ for 10 hz to 60 hz motor speed. Compressor operation by motor with 10 to 60 hz were resulted in reduction of pressure pulsation from 16.415% to 35.151%. Pressure losses were varied from $0.001%{\sim}0.759%$, and pressure drop per centimeter of the steel pipe were varied from $0.0160{\sim}16.03\;Pa$.

• Journal of Mechanical Science and Technology
• /
• 제15권3호
• /
• pp.366-373
• /
• 2001

A numerical analysis of shock wave/boundary layer interaction in transonic/supersonic axial flow compressor cascade has been performed by using a characteristics upwind Navier-Stokes method with various turbulence models. Two equation turbulence models were applied to transonic/supersonic flows over a NACA 0012 airfoil. The results are superion to those from an algebraic turbulence model. High order TVD schemes predicted shock wave/boundary layer interactions reasonably well. However, the prediction of SWBLI depends more on turbulence models than high order schemes. In a supersonic axial flow cascade at M=1.59 and exit/inlet static pressure ratio of 2.21, k-$\omega$ and Shear Stress Transport (SST) models were numerically stables. However, the k-$\omega$ model predicted thicker shock waves in the flow passage. Losses due to shock/shock and shock/boundary layer interactions in transonic/supersonic compressor flowfields can be higher losses than viscous losses due to flow separation and viscous dissipation.