• 에너지공학
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• 제11권2호
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• pp.90-98
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• 2002

본 연구는 선회유동과 연소인자가 9.4L인 터보과급 디젤엔진의 성능과 배기가스특성에 미치는 영향을 실험적으로 고찰하였다. 일반적으로 디젤엔진의 연소과정에서 선회유동은 분사되고 있는 연료와 흡칩공기의 혼합을 촉진시켜 줌으로써 엔진성능을 향상시키는데 매우 중요한 인자가 된다. 특히 터보과급 디젤엔진에서는 실린더내의 고온.고압가스로 인하여 연비와 NO$_{x}$ 농도는 서로 상반관계를 가지므로 적절한 용량의 과급기선정으로 흡.배기시스템, 분사시스템 및 연소실의 설계 등을 고려할 필요가 있다. 본 연구의 결과로서, 정상유동실험을 통하여 선회비가 증가함으로써 평균유량계수가 감소하고, 반면에 걸프 펙터가 증가함을 알 수 있었다. 또한 엔진실험을 통하여 흡기포트의 선회비 2.43, 분사시기 BTDC 13$^{\circ}$ CA, 압축비 16, 리앤트란트 5$^{\circ}$형 연소실, 노즐분공경 $\Phi$0.28*6 및 과급기 GT40(압축기 A/R 0.58, 터빈 A/R 1.19)의 적용인자가 최적의 성능 및 배기가스를 만족시킬 수 있었다.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2011년도 춘계학술대회 초록집
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• pp.222-222
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• 2011

Plastic product is increasing by the growth of its demand and most of refused plastics are incinerated or reclaimed. However, the refused plastic is not easily decomposed and has the environmental problem with its various toxic gas in case of incineration. Therefore, many countries such as USA, Japan, Germany and other developed industrial countries as well as Korea are interested in studying the recyclable resource of refused plastic. The macromolecular waste pyrolysis has the advantage of collecting of raw materials in high price and can at least get fuel gas or oil with high heat capacity. It also discharges low waste gas and low toxic gas including SOx, NOx and HCl heavy metals. However, pyrolyzed oil includes enough excess unsaturated hydrocarbons to form tar, which can cause the nozzle of engines to plug when pyrolyzed oil is used as fuel. Activated carbon was proven to have prominent adsorption capability among the other adsorbents that were mainly composed of carbon. This study examined the possibility of application in activated charcoal of its solid formation by analysing the feature of pyrolysis which is one of the chemical recycling methods and getting chemical analysis of the product and activated energy. Analyze the element of the oil produced by pyrolysis using GC-MS. The experiment of tar adsorption using fly-ash showed that fly-ash improved the optical intensity of pyrolyzed oil and decreased oxygen compounds in the pyrolyzed oil.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2003년도 춘계학술대회 논문집
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• pp.764-767
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• 2003

The characteristics of diesel spray have much effect on the engine performances such as power. fuel consumption rate and emissions. Therefore, the measurement of fuel spray characteristics is very important for the improvement of heat engine. The factors which control diesel spray characteristics are injection pressure, ambient temperature and density etc. Spray behaviors are visualized by using the high speed video camera and spray angle, spray penetration are measured. Experimental equations of spray penetration and spray angle were derived by using the experimental results. 1) Ambient temperature and density influence on the characteristics of diesel spray. 2) Experimental equation of spray penetration is expressed as follows 0＜t＜ $t_{b}$ ; $S_1$=11.628$\Delta$ $P^{0.485}$ $\rho$$_{a}$ $^{-0.478}$ $t^{1.337}$, $t_{b}$ ＜t; $S_2$=7.457$\Delta$ $P^{0.523}$ $\rho$$_{a}$ $^{-0.382}$ $t^{0.548}$ 3) Experimental equation of spray Angie is expressed as follows $T_{a}$ =293K; Tan($\theta$/2)=059($\rho$$_{a}$ / $\rho$$_{f}$ )$^{0.437}$, $T_{a}$ =473K; Tan($\theta$/2)=0588($\rho$$_{a}$ / $\rho$$_{f}$ )$^{0.404}$_{f}$ )$^{0.404}$

• 대한기계학회논문집B
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• 제37권2호
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• pp.139-148
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• 2013

본 연구에서는 1kW 급 SOFC 시스템의 AOGR(anode off-gas recirculation)을 위한 이젝터를 설계하고 이젝터 적용시의 시스템 효율을 매개변수 연구를 통해 알아보았다. 화공해석 프로그램를 이용하여 이젝터의 작동 조건을 계산하였고, 전역 최적값을 보장하면서도 CFD 계산에 따른 부하를 최소화하기 위하여 유전 알고리듬과 크리깅 모델을 이용하여 최적화를 진행하였다. 최적화를 통해 음속 이젝터에서 가장 큰 영향을 미치는 설계 변수가 이젝터의 목직경과 1 차 노즐의 위치임을 식별하였다. 유동변수에 대한 매개변수 연구를 통해 설계된 이젝터는 1kW 급 SOFC 의 다양한 작동 조건에서 충분한 유연성을 가지며, SOFC 에 적용시 증기의 56% 와 연료의 8.4% 절감이 가능함을 보였다.

• 한국추진공학회지
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• 제9권4호
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• pp.48-54
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• 2005

액체 산소(LOx)와 Jet A-1(Jet engine fuel)을 추진제로 하는 소형 액체 로켓 연소기에서 막 냉각의 효과에 관한 실험적 연구를 수행하였다. 막 냉각제(Jet A-1과 물)는 막냉각장치를 통해 분사되도록 하였다. 막 냉각 유량 변화에 따른 연소기의 외벽온도 및 막 냉각 길이는 추진제 혼합비, 연소실 압력 및 막냉각장치의 형상 변화(분사각)에 따라 비교하였다. 막 냉각에 따른 특성속도 효율의 손실도 막 냉각제를 물과 Jet A-1을 사용하였을 경우에 대해서 각각 구하였다. 연소실 압력의 증가에 따라 노즐에서의 외벽 온도는 증가하였으나, 퍼센트 막냉각 유량이 9% 이상인 경우에 연소실에서는 거의 영향을 받지 않았다. 특성속도는 퍼센트 막냉각 유량이 9% 이상일 때 추진제 혼합비에 영향을 받지 않았다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제29회 추계학술대회논문집
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• pp.354-358
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• 2007

초소형 터보제트엔진에 적용되는 슬링거 인젝터 시스템의 분무특성을 파악하기 위한 연구를 수행 하였다. 이 연료 분사시스템은 엔진의 회전축으로부터 발생된 원심력에 의하여 연료가 연소기 내부로 공급되고, 액체연료의 미립화를 초래한다. 시험장치는 고속으로 회전하는 Spindle, 슬링거 인젝터, 가압식 물탱크, 아크릴 케이스로 구성하였다. 분무입자의 크기 및 속도를 측정하기 위해 PDPA(Phase Doppler Particle Analyzer) 시스템을 사용하였고, Nd-Yag Laser를 광원으로 사용하여 분무를 가시화 하였다. 시험결과 SMD(Sauter Mean Diameter)는 회전수, 유량, Injection Orifice 수에 큰 영향을 받는 것으로 나타났다. 이러한 실험적 연구로부터 이 시스템의 분무특성을 이해할 수 있었고, 초소형 터보제트엔진에 적합한 슬링거 인젝터의 형성을 도출할 수 있었다.

• Journal of Mechanical Science and Technology
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• 제19권5호
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• pp.1194-1205
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• 2005

The common-rail injection systems, as a new diesel injection system for passenger car, have more degrees of freedom in controlling both the injection timing and injection rate with the high pressure. In this study, a piezo-driven injector was applied to a high pressure common-rail type fuel injection system for the control capability of the high pressure injector's needle and firstly examined the piezo-electric characteristics of a piezo-driven injector. Also in order to analyze the effect of injector's needle response driven by different driving method on the injection, we investigated the diesel spray characteristics in a constant volume chamber pressurized by nitrogen gas for two injectors, a solenoid-driven injector and a piezo-driven injector, both equipped with the same injection nozzle with sac type and 5-injection hole. The experimental method for spray visualization was based on back-light photography technique by utilizing a high speed framing camera. The macroscopic spray propagation was geometrically measured and characterized in term of the spray tip penetration, spray cone angle and spray tip speed. For the evaluation of the needle response of the above two injectors, we indirectly estimated the needle's behavior with an accelerometer and injection rate measurement employing Bosch's method was conducted. The experimental results show that the spray tip penetrations of piezo­driven injector were longer, on the whole, than that of the solenoid-driven injector. Besides we found that the piezo-driven injector have a higher injection flow rate by a fast needle response and it was possible to control the injection rate slope in piezo-driven injector by altering the induced current.

• 한국추진공학회지
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• 제20권6호
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• pp.83-90
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• 2016

이중 모드 램젯 엔진 모델의 램젯 모드 연소 시험을 수행하였다. 엔진 모델은 흡입구, 연소기 및 노즐로 이루어졌다. 로켓 기반 복합 사이클 엔진에 사용하는 것을 전제로 큰 후향 계단을 가지는 형상을 선택하였다. 시험은 마하 5, 고도 24 km 조건에서 수행하였다. 연료를 카울면과 바닥면에 분산하여 다중 분사를 한 경우에 안정적인 연소를 달성할 수 있었다. 또한 연료 당량비를 카울면에서 0.5, 바닥면에서 0.5로 하여 총 당량비 1.0으로 한 경우에 연소기 내부에서 열질식이 발생하여 유동이 아음속으로 조성되는 램젯 모드로 운전됨을 확인하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.109-114
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• 2008

This paper presents the development status of a subscale precooled turbojet engine "S-engine" for the hypersonic cruiser and space place. S-engine employs the precooled-cycle using liquid hydrogen as fuel and coolant. It has $23cm{\times}23cm$ of rectangular cross section, 2.6 m of the overall length and about 100 kg of the target weight employing composite materials for a variable-geometry rectangular air-intake and nozzle. The design thrust and specific impulse at sea-level-static(SLS) are 1.2 kN and 2,000 sec respectively. After the system design and component tests, a prototype engine made of metal was manufactured and provided for the system firing test using gaseous hydrogen in March 2007. The core engine performance could be verified in this test. The second firing test using liquid hydrogen was conducted in October 2007. The engine, fuel supplying system and control system for the next flight test were used in this test. We verified the engine start-up sequence, compressor-turbine matching and performance of system and components. A flight test of S-engine is to be conducted by the Balloon-based Operation Vehicle(BOV) at Taiki town in Hokkaido in October 2008. The vehicle is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high-altitude observation balloon. After 40 second free-fall, the vehicle pulls up and S-engine operates for 60 seconds up to Mach 2. High altitude tests of the engine components corresponding to the BOV flight condition are also conducted.