• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.91-93
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• 2003

A comprehensive numerical study is carried out to investigate for the understanding of the flow evolution and flame development in a supersonic combustor with normal injection of ncumally injecting hydrogen in airsupersonic flows. The formulation treats the complete conservation equations of mass, momentum, energy, and species concentration for a multi-component chemically reacting system. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations and detailed chemistry of H2-Air is considered. It also accommodates a finite-rate chemical kinetics mechanism of hydrogen-air combustion GRI-Mech. 2.11[1], which consists of nine species and twenty-five reaction steps. Turbulence closure is achieved by means of a k-two-equation model (2). The governing equations are spatially discretized using a finite-volume approach, and temporally integrated by means of a second-order accurate implicit scheme (3-5).The supersonic combustor consists of a flat channel of 10 cm height and a fuel-injection slit of 0.1 cm width located at 10 cm downstream of the inlet. A cavity of 5 cm height and 20 cm width is installed at 15 cm downstream of the injection slit. A total of 936160 grids are used for the main-combustor flow passage, and 159161 grids for the cavity. The grids are clustered in the flow direction near the fuel injector and cavity, as well as in the vertical direction near the bottom wall. The no-slip and adiabatic conditions are assumed throughout the entire wall boundary. As a specific example, the inflow Mach number is assumed to be 3, and the temperature and pressure are 600 K and 0.1 MPa, respectively. Gaseous hydrogen at a temperature of 151.5 K is injected normal to the wall from a choked injector.A series of calculations were carried out by varying the fuel injection pressure from 0.5 to 1.5MPa. This amounts to changing the fuel mass flow rate or the overall equivalence ratio for different operating regimes. Figure 1 shows the instantaneous temperature fields in the supersonic combustor at four different conditions. The dark blue region represents the hot burned gases. At the fuel injection pressure of 0.5 MPa, the flame is stably anchored, but the flow field exhibits a high-amplitude oscillation. At the fuel injection pressure of 1.0 MPa, the Mach reflection occurs ahead of the injector. The interaction between the incoming air and the injection flow becomes much more complex, and the fuel/air mixing is strongly enhanced. The Mach reflection oscillates and results in a strong fluctuation in the combustor wall pressure. At the fuel injection pressure of 1.5MPa, the flow inside the combustor becomes nearly choked and the Mach reflection is displaced forward. The leading shock wave moves slowly toward the inlet, and eventually causes the combustor-upstart due to the thermal choking. The cavity appears to play a secondary role in driving the flow unsteadiness, in spite of its influence on the fuel/air mixing and flame evolution. Further investigation is necessary on this issue. The present study features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the previous works. In particular, the oscillatory flow characteristics are captured at a scale sufficient to identify the underlying physical mechanisms. Much of the flow unsteadiness is not related to the cavity, but rather to the intrinsic unsteadiness in the flowfield, as also shown experimentally by Ben-Yakar et al. [6], The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The work appears to be the first of its kind in the numerical study of combustion oscillations in a supersonic combustor, although a similar phenomenon was previously reported experimentally. A more comprehensive discussion will be given in the final paper presented at the colloquium.

• 한국식품영양과학회지
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• 제38권3호
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• pp.338-345
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• 2009

미강유(RBO), 팜스테아린(PS), 고올레인산 해바라기씨유(HO)를 기질로 사용하여 24 hr, $65^{\circ}C$의 조건하에 회분식 반응기(batch type reactor)에서 TLIM을 이용한 interesterification을 통해 생성된 저트랜스 쇼트닝의 이화학적 특성을 살펴보았다. DSC 분석결과를 살펴보면, SFC 함량 변화는 commercial shortening과 low-trans shortening(LTS) 간에 거의 유사하게 측정되었고, slip melting point는 각각 35.5, $34.8^{\circ}C$로 나타났다. 지방산 조성 분석 결과, LTS는 전체 지방산 조성의 90% 이상이 C16:0(33.7 wt%), C18:1(45.7 wt%), C18:2(13.4 wt%)로 구성되어 있으며 이 중 트랜스지방산은 시중 유통 쇼트닝보다 3배 이상 적은 0.5 wt%로 미량 검출되었다. Sn-2 position에 위치한 지방산 조성은 C16:0이 36.6 wt%, C18:1이 43.5 wt%로 나타났다. LTS의 주요 TAG 조성으로는 POO, POP, PLO 등으로 나타났고, 반응 전과 반응 후의 TAG 조성을 비교해 보면, OOO와 PPP의 area%는 각각 27.65에서 6.97 area%로, 11.97에서 3.36 area%로 감소한 반면 POO는 15.94에서 29.05 area%로, PLO는 6.44에서 13.05 area%로 증가되었다. ${\alpha},\;{\gamma}\;{\delta}$-Tocopherol 분석 결과 LTS의 total tocopherol은 12.37 mg/100 g, ${\gamma}$-oryzanol 함량은 0.43 mg/100 g을 나타냈으며, total phytosterol 함량은 251.38 mg/100 g으로 나타났다. Commercial shortening과 LTS의 texture analyzer를 통한 hardness 측정 결과, commercial shortening은 157.41 g, LTS는 157.00 g으로 두 시료의 hardness가 비슷하게 측정되었다. LTS의 polymorphic form을 측정하기 위해 x-ray duffraction을 사용하였다. 일반적으로 쇼트닝이나 마가린은 ${\beta}'$형 결정일 때 바람직하다고 여겨지는데, LTS의 분석 결과 ${\beta}$형이 함께 공존하고 있지만, ${\beta}'$형이 우세하게 나타났다.