• 한국분말재료학회지
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• 제17권1호
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• pp.29-35
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• 2010

We produced cylindrical porous TiNi bodies by Self-propagating High-temperature Synthesis (SHS) process, varying the heating schedule prior to ignition of a loose preform compact made from (Ti+Ni) powder mixture. To investigate the effect of the heating schedule on the behaviour of combustion wave propagation and the structure of porous TiNi shape-memory alloy (SMA) body, change of temperature in the compact during SHS process was measured as a function of time and used for determining combustion temperature and combustion wave velocity. Microstructure of produced porous TiNi SMA body was observed and the results were discussed with the combustion characteristics. From the results it was concluded that the final average pore size could be controlled either by the combustion wave velocity or by the average temperature of the preform compact prior to ignition.

• 대한기계학회논문집
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• 제19권8호
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• pp.1989-1998
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• 1995

Characteristics of the flame propagation for normal and abnormal combustion in hydrogen premixture in a cylindrical constant-volume combustion chamber are studied numerically. A detailed hydrogen oxidation kinetic mechanism, mixture transport properties and a model describing spark ignition process are used. The calculated pressure-time history of the stable deflagration wave propagation agrees well with the experiment. The ignition of the premixture in the unburned gas, initiated by the hot spot, causes a transition from deflagration to detonation under some initial temperature and pressure. Under the initial conditions with high temperature and pressure, excessive ignition energy initiates a strong blast wave and a detonation wave that follows. The chemical reaction in the detonation wave is much more vigorous than that in the deflagration wave and the peak pressure in the detonation wave is much higher than the equilibrium value.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.628-631
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• 2017

정상초음파가 인가된 탄화수소계 연료별/공기 혼합물의 당량비에 따른 연소특성 비교를 실험적 연구 결과로 제시한다. 전파화염의 이미지는 고속카메라를 이용하여 획득하였으며, 이미지 후처리를 통해 연료별 연소특성을 면밀히 관찰하였다. 정상초음파를 인가하면 탄화수소계 연료/공기 예혼합기의 이론당량비조건에서 연소반응을 촉진시킨다는 점을 확인하였다.

• 한국세라믹학회지
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• 제31권11호
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• pp.1249-1258
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• 1994

Titanium carbide was synthesized by reacting the prepared titanium powder and carbon black using SHS method sustains the reaction spontaneously, utilizing heat generated by the exothermic reaction itself. In this process, the effect of the particle size of titanium powder on combustion temperature and combustion wave velocity was investigated. By controlling combustion temperature and combustion wave velocity via mixing Ti and C powder with TiC, the reaction kinetics of TiC formation by SHS method was considered. Without reference to the change of combustion temperature and combustion wave velocity, TiC was easily synthesized by combustion reaction. As the particle size of titanium powder was bigger, or, as the amount of added diluent(TiC) increased, combustion temperature and combustion wave velocity were found to be decreased. The formation of TiC by combustion reaction in the Ti-C system seems to occur via two different mechanisms. At the beginning of the reaction, when the combustion temperatures were higher than 2551 K, the reaction was considered to be controlled by the rate of dissolution of carbon into a titanium melt with an apparent activation energy of 148 kJ/mol. For combustion temperatures less than 2551 K, it was considered to be controlled by the atomic diffusion rate of carbon through a TiC layer with an apparent activation energy of 355 kJ/mol. The average particle size of the synthesized titanium carbide was smaller than that of the starting material(Ti).

• Advances in aircraft and spacecraft science
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• 제7권3호
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• pp.187-202
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• 2020

The exhaust nozzle serves back pressure of Pulse detonation combustor, so combustion chamber gets sufficient pressure for propulsion. In this context recent researches are focused on influence of nozzle effect on single cycle detonation wave propagation and propulsion performance of PDE. The effects of various nozzles like convergent-divergent nozzle, convergent nozzle, divergent nozzle and without nozzle at exit section of detonation tubes were computationally investigated to seek the desired propulsion performance. Further the effect of divergent nozzle length and half angle on detonation wave structure was analyzed. The simulations have been done using Ansys 14 Fluent platform. The LES turbulence model was used to simulate the combustion wave reacting flows in combustor with standard wall function. From these numerical simulations among four acquaint nozzles the highest thrust augmentation could be attained in divergent nozzle geometry and detonation wave propagation velocity eventually reaches to 1830 m/s, which is near about C-J velocity. Smaller the divergent nozzle half angle has a significant effect on faster detonation wave propagation.

• 대한기계학회논문집B
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• 제27권8호
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• pp.1191-1199
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• 2003

This paper describes to observe the combustion process of only one droplet cluster. In this study, liquid fuel was atomized by ultrasonic wave to form an acoustically levitated droplet cluster. In order to elucidate the detailed structure of burning process of the droplet cluster, laser tomography method was applied. Time-series planar images of fuel droplets were processed and diameter of the each droplet was calculated based on the Mie-scattering theory. Using these data, the modified droplet group combustion number was estimated in time-series. As the result, when the internal droplet group combustion occur, the modified group combustion number dose not decrease monotonically, but show a tow-staged decreasing process. In all case of combustion process, combustion reactions were measured two types that combustion speed was fast and slow. It was casued by difference of concentration degree and droplet size distribution.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.565-572
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• 2004

Numerical stability analysis of one-dimensional axial flow in solid rocket motors is performed based on the Euler equation coupled with an unsteady combustion equation of solid propellant. In order to check the numerical scheme, behavior of a standing wave in a closed tube is examined. A standing wave in solid rocket motor decays or grows depending on the total effect of propellant combustion, nozzle flow, and so on. The stability boundary of the fundamental mode standing wave is determined by changing one of the combustion parameters. In addition growth rates of the wave are calculated numerically in relatively low Mach number flow region for the motors with different port and nozzle throat diameters. The results obtained here agree well with the approximate solution. The same scheme is applied to a motor with shorter length and L＊-instability is observed.

• 한국산학기술학회논문지
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• 제21권8호
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• pp.401-406
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• 2020

자동차에서 배출되는 배기가스 중 질소산화물은 요사이 문제가 되는 미세먼지의 주요 요인 중 하나이다. 질소산화물(NOx)은 고온 조건에서 연소가 진행될 때 발생하므로 연소시 온도를 낮추는 방법으로 발생을 억제하고 있다. 자동차에서는 일반적으로 배기가스 재순환(EGR)을 사용하여 연소 온도를 낮추는 방법으로 감소시킨다. 그러나 EGR 비율이 높아질수록 NOx의 양은 저감되나 연소 안정성의 하락으로 인한 불완전연소 가능성의 증가로 일산화탄소와 미연탄화수소의 양이 증가하여 오히려 오염물질이 증가하는 문제를 발생시킬 수 있다. 여기에서는 연료 입자에 음파를 조사하여 연료 입자의 운동성을 향상시켜 연소가 원활히 진행되게 하여 연소의 안정성을 향상시키는 방안에 대하여 해석적 및 실험적 방법으로 연구하였다. 해석적 방법으로는 유동해석 소프트웨어를 사용하여 연료 입자에 다양한 주파수의 음파를 조사하여 연료 입자의 움직임 변화에 대한 연구를 진행하였다. 해석 결과, 작은 연료 입자의 조건에서는 고주파의 음파에 의해 영향을 많이 받고, 연료 입자가 큰 조건에서는 저주파의 음파에 의해 영향을 많이 받아 운동성이 증가함을 알 수 있었다. 실험적 방법으로는 연소실을 구성하여 정해진 당량비 조건에서 연소시키며 다양한 주파수의 음파를 조사하며 연소실내 압력을 측정하는 연구를 진행하였다. 측정된 압력으로부터 열방출량을 계산하면 연소의 진행 상황에 대한 정보를 얻을 수 있는데, 실험 결과 초기 연소시 상대적 저주파 조사 조건에서 열방출량이 증가한 것을 확인할 수 있었다.

• 한국항공우주학회지
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• 제33권3호
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• pp.99-106
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• 2005

액체로켓엔진 개발에서 필수 단계인 연소안정성 확인을 위한 연소안정성 평가시험(stability rating test) 방법의 개발을 위해서는 압력교란장치의 특성과 더불어 안전한 연소시험 절차(sequence)의 확립이 필수적이다. 따라서 본 연구에서는 연소안정성 평가시험을 위해 개발된 펄스건을 액체로켓엔진의 연소시험에 실제로 적용하기 위한 단계로서, 적절한 연소 시험 절차를 개발/검증하고자 하였다. 먼저 펄스건을 실제로 연소실 외벽에 장착하게 되는 압력파 유도장치를 설계하고, 펄스건의 오작동을 방지하기 위한 압력파 유도장치 내부의 냉각시스템의 설계 및 시험을 수행하였다. 이러한 일련의 연소시험 단계를 통하여 실물형 액체로켓엔진에서의 연소안정성 평가시험이 가능한 적절한 시험 단계를 국내 독자적으로 개발하는데 성공하였다.

• Advances in aircraft and spacecraft science
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• 제10권3호
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• pp.203-222
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• 2023

The detonation combustion is a supersonic combustion process follows on shock wave oscillations in detonation tube. In this paper numerical studies are carried out combined effect of blockage ratio and spacing of obstacle on detonation wave propagation of hydrogen-air mixture in pulse detonation combustor. The deflagration to detonation transition of stoichiometric (ϕ=1)fuel-air mixture in channel has been analyzed for effect of blockage ratio (BR)=0.39, 0.51, 0.59, 0.71 with spacing of 2D and 3D. The reactive Navier-Stokes equation is used to solve the detonation wave propagation mechanism in Ansys Fluent platform. The result shows that fully developed detonation wave initiation regime is observed near smaller vortex generator ratio of BR=0.39 inside the combustor. The turbulent rate of reaction has also a great significance role for shock wave structure. However, vortices of rapid detonation wave are appears near thin boundary layer of each obstacle. Finally, detonation combustor demonstrates the superiority of pressure gain combustor with turbulent rate of reaction of 0.6 kg mol/m3 -s inside the detonation tube with obstacle spacing of 12 cm, this blockage enhanced the turbulence intensity and propulsive thrust. The successful detonation wave propagation speed is achieved in shortest possible time of 0.031s with a significance magnitude of 2349 m/s, which is higher than Chapman-Jouguet (C-J) velocity of 1848 m/s. Furthermore, stronger propulsive thrust force of 36.82 N is generated in pulse time of 0.031s.