• 터널과지하공간
• /
• 제2권1호
• /
• pp.116-122
• /
• 1992

A comprehensive, nonsteady state, computer simulation program for the environmental conditions in advancing tunnels (the HEADSIM simulation program) is constructed and successfully validated with heat balance amongst all heat sources, and with mass conservation amongst various airflows including the leakage air from ducts, under timedependent variations of inlet air conditions. which include sudden, diurnal and seasonal changes. Heat conduction in the wall strata and face strata is simulated with most complicated boundary conditions using the finite difference method, and the climatic conditions in roadway sections which contain air ducts, booster fan, spray cooler, compressed air pipes, cold water pipes, return water pipes, machinery and broken rock are simulated taking into account the variations of face operation and the heat storage mechanism in the strata. The limitations of simulation time steps and roadway section lengths are defined according to the stability criteria satisfying the principles of thermodynamics. Variations of heat transfer coefficients, which are newly set, and those of wetness factors are taken into account according to the variations of other parameters and the stepwise advance of the face. Newly-derived formulae are used for computing the air duct leakage and the pressure inside of the duct. A new concept of an 'imaginary duct' is introduced to simulate the climatic conditions in tunnels during holiday periods, which directly affect conditions on subsequent working days under the consideration of natural convection. A subsidiary program (the WALLSIM simulation program) is made to compute the dimensionless tunnel surface temperatures and to compare the results with those from analytical approaches, and to demonstrate the stability, convergence and accuracy of the strata heat conduction simulation, adopting the finite difference method. The WALLSIM also has wide applications, including those for the computation of age coefficients.

• 한국유체기계학회 논문집
• /
• 제12권3호
• /
• pp.44-52
• /
• 2009

Small scale steam turbines are used as mechanical drivers in chemical process plant or power generators. In this study, a design technology was developed for a 100kW class steam turbine which will be used for removing $CO_2$ from the emission gas on a reheated cycle system. This turbine is operated at a low inlet total pressure of $5\;kgf/cm^2$. It consists of two stages and operates at the partial admission. For the meanline analysis, a performance prediction method was developed and it was validated through the performances on the operating small steam turbines which are using at plants. Their results showed that the output power was predicted within 10% deviation although the steam turbines adopted in this analysis were operated at different flow conditions and rotor size. The turbine blades was initially designed based on the computed results obtained from the meanline analysis. A supersonic nozzle was designed on the basis of the operating conditions of the turbine, and the first stage rotor was designed using a supersonic blade design method. The stator and second stage rotor was designed using design parameters for the blade profile. Finally, Those blades were iteratively modified from the flow structures obtained from the three-dimensional flow analysis to increase the turbine performance. The turbine rotor system was designed so that it could stably operate by 76% separation margin with tilting pad bearings.

• 한국입자에어로졸학회지
• /
• 제13권3호
• /
• pp.119-125
• /
• 2017

A novel two stage cylindrical cyclone was developed for a 3 phase separator in shale oil production industry. The cyclone performance was compared with a cone type cyclone and multi cyclone at the same experimental condition using water and oil mists generated by a humidifier and atomizer at the flow rate 1 to $2m^3/min$. The removal efficiency of total suspended water droplets by the novel cyclone, calculated using inlet and outlet concentrations measured by an optical particle counter, was 99% which is higher than 90% of oil droplet removal efficiency at $2m^3/min$. It might be due to the evaporation of small water droplets during the tests. The water and oil droplet removal performance of the novel cyclone based on the quality factor which is a function of pressure drop and removal efficiency was the highest among three cyclones. The results indicate that the cyclone could be an economical device to remove water and oil mists from shale gas generation processes where a huge three phase separator is commonly used.

• 항공우주기술
• /
• 제9권2호
• /
• pp.63-72
• /
• 2010

발사체 추진시스템에서 CC(Combustion Chamber) 산화제 개폐밸브는 액체산소를 연소기로 공급 및 차단함으로써 연소를 개시 및 중단시킬 뿐만 아니라, 정상운영 상태에서는 연소기 내 안정된 연소가 가능하도록 일정한 유량의 액체산소를 공급한다. TM(Technology Model)에 비해 높은 유출계수를 가지는 EM(Engineering Model)이 전반적인 요구 성능을 만족하는 것으로 나타났지만, 성능 향상을 위해 EM의 주요 부분에 대한 추가적인 설계 변경을 수행하였다. 공압 제어부, 중간 플랜지, 그리고 밸브 입구의 립 부분의 형태를 설계 변경하였으며, 해당 시험 시제를 제작하여 성능시험을 수행하였다. 이러한 성능 시험을 통해 의도했던 성능 향상이 이루어진 것을 최종 확인하였다.

• 대한기계학회논문집B
• /
• 제26권6호
• /
• pp.805-810
• /
• 2002

Development of a small gas-turbine combustor for 100㎾ class APU(Auxiliary Power Unit) has been performed. This combustor is a reverse-annular type and has a tangential swiller in the liner head to improve the fuel/air mixing and flame stability. Three main and three pilot fuel injectors of the simplex pressure-swirl type are used. The performance target at the design condition includes a turbine inlet temperature of l170k, a combustion efficiency of 99%, a pattern factor of 30%, and an engine durability of 3000 hours. Under developing the combustor, we conducted the performance test of our first prototype(TS1) with some variants. As a result of the test, the performance targets of the combustor are satisfied except that the pattern factor is about 4% higher than the target value. Therefore, the second prototype(TS2) was redesigned and the performance test was conducted with the critical focus on the pattern factor and the exit mean temperature. We adopted TS2 four variants to check the improvement of the pattern factor. As a result, the pattern factors of several variants were satisfied with the performance target. Finally, the TS2A variant was chosen as a final combustor fur our APU model.

• Journal of Advanced Marine Engineering and Technology
• /
• 제36권8호
• /
• pp.1050-1060
• /
• 2012

SOFC시스템 고효율화의 한 방법으로 SOFC/GT 하이브리드시스템은 유효하다. 그러나 시스템의 출력 규모가 수십 MW급의 선박용이라면 하부시스템으로 사용되는 GT시스템의 냉각방식 도입은 장치를 복잡하게 만들고 제어 또한 쉽지 않게 된다. 따라서 선박용으로는 SOFC/GT(유냉각) 하이브리드시스템보다 SOFC/GT(무냉각) 하이브리드시스템이 더 적합해 보인다. 본 연구는 SOFC/GT(무냉각) 하이브리드시스템을 구축하고 그 시스템에 대한 스택의 작동온도와 전류밀도, 가스터빈의 압력비, TIT가 시스템의 성능에 미치는 영향 등을 시뮬레이션을 통하여 검토한 것으로 공기압축기 소요 동력의 증가에도 불구하고 전기적 효율은 상승되며 TIT에는 운전을 위한 제한된 온도범위가 존재한다는 것을 알 수 있었다.

• Journal of Mechanical Science and Technology
• /
• 제18권8호
• /
• pp.1435-1450
• /
• 2004

Experimental data are presented which describe the effects of a combustor-level high free-stream turbulence on the near-wall flow structure and heat/mass transfer on the endwall of a linear high-turning turbine rotor cascade. The end wall flow structure is visualized by employing the partial- and total-coverage oil-film technique, and heat/mass transfer rate is measured by the naphthalene sublimation method. A turbulence generator is designed to provide a highly-turbulent flow which has free-stream turbulence intensity and integral length scale of 14.7% and 80mm, respectively, at the cascade entrance. The surface flow visualizations show that the high free-stream turbulence has little effect on the attachment line, but alters the separation line noticeably. Under high free-stream turbulence, the incoming near-wall flow upstream of the adjacent separation lines collides more obliquely with the suction surface. A weaker lift-up force arising from this more oblique collision results in the narrower suction-side corner vortex area in the high turbulence case. The high free-stream turbulence enhances the heat/mass transfer in the central area of the turbine passage, but only a slight augmentation is found in the end wall regions adjacent to the leading and trailing edges. Therefore, the high free-stream turbulence makes the end wall heat load more uniform. It is also observed that the heat/mass transfers along the locus of the pressure-side leg of the leading-edge horseshoe vortex and along the suction-side corner are influenced most strongly by the high free-stream turbulence. In this study, the end wall surface is classified into seven different regions based on the local heat/mass transfer distribution, and the effects of the high free-stream turbulence on the local heat/mass transfer in each region are discussed in detail.

• 대한기계학회논문집B
• /
• 제23권8호
• /
• pp.1048-1062
• /
• 1999

A numerical method and experiments for the aerodynamic design of high performance two-stage axial flow fans was carried out. A vortex ring element method used for the aerodynamic analysis of the propellers was extended to the fan-duct system. Fan Performance and velocity profiles at the fan inlet and outlet are compared with experimental data for the validations of numerical method. Performance test was done based on KS B 6311(testing methods for turbo-fans and blowers). The velocity profile was obtained using a 5-hole pitot tube by the non-nulling method. The two stage axial flow fan configurations for the optimal operation conditions were set by using the experimental results for the single rotating axial flow fan and the single stage axial flow fan. The single rotating axial flow fan showed relatively low efficiency due to the swirl velocities behind rotor exit which produced pressure losses. In contrast, the single stage and the two-stage axial flow fans showed performance improvements due to the swirl velocity reduction by the stator. The peak efficiency of the two stage axial flow fan was improved by 21% and 6%, compared to the single rotating axial flow fan and the single stage axial flow fan, respectively.

• 대한기계학회논문집B
• /
• 제39권3호
• /
• pp.207-214
• /
• 2015

해양온도차발전용 터빈의 효율과 크기를 파악하기 위해 R134a를 작동유체로 하고 출력 5 kW인 반경류형 터빈의 설계가 수행되었다. 터빈입구온도 $25^{\circ}C$, 출구 정압 4.9 bar, 질량유량 1.16 kg/s 로 설정하고 평균유동해석을 수행하여 터빈의 회전수와 주요 치수를 결정하였다. 이들을 바탕으로, 3 차원 터빈 모델을 구축하였으며, 도출된 터빈회전수 12,820 rpm에 대하여 전산유체역학(CFD) 소프트웨어 ANSYS CFX를 이용하여 볼류트와 노즐을 포함하는 터빈 내부 유동장 특성과 효율이 조사되었다. 80%이상의 터빈 효율이 적정 범위 내의 노즐 안내깃 수(10-15 개)에서 제시되었으며, 가장 높은 터빈 효율은 15 개의 안내 깃에서 나타났다.

• 한국항공우주학회지
• /
• 제43권7호
• /
• pp.619-625
• /
• 2015

스월 인젝터는 액체로켓 엔진에서의 연료 분사 장치로 널리 사용되고 있으며, 이에 따른 연구 또한 활발하게 진행되고 있다. 특히 연소 불안정 문제를 해결하는 것은 모든 종류의 액체로켓 엔진에서 필수적이다. 본 연구에서는 연소불안정을 해결하기 위한 기초 연구로 오픈형 스월 인젝터에 대한 수류실험을 수행하였다. 인젝터로 유입되는 작동유체에 압력 섭동을 발생시키고, 그에 따른 응답특성을 실험적으로 파악하였다. 또한, 인젝터 스월 챔버의 길이와 지름을 변화시킴으로써 인젝터 구조의 변화에 따른 응답 특성의 변화를 확인하였다.