• 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.

• 자원환경지질
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• 제34권4호
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• pp.329-343
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• 2001

국내에서 가장 높은 용출온도를 보이는 경남 부곡 지열수에 대하여 Yun et al.(1998)에 의하여 기존에 발표된 수리화학 및 동위원소 자료를 토대로 지열수의 심부환경과 지화학적 진화과정을 재해석하였다. 부곡 지열수는 지화학적 특성에 따라 3가지 유형으로 구분되어 진다(지열수I,II,III형). 지열수I형과II형은 높은 온도(55.2~$77.2^{\circ}C$)를 보이며, 화학적으로 Na-$SO_4$형에 속하지만, pH와 Eh가 다소 차이가 나며, $SO_4$함량이 크다는 것이 특징이다. 지열수 중심지역으로부터 외곽부에서 산출되는 지열수 III형은 29.3~$47.0^{\circ}C$의 용출온도를 보이며, Na-$HCO_3SO_4$형을 나타낸다. 지열수 I형에 대하여 다성분계 지질온도계의 적용결과는 심부저장지의 온도가 115~$130^{\circ}C$인 것으로 추정되었다. 다양한 지화학적 특성을 보여주는 부곡 지열수의 지화학적 진화과정은 다음과 같이 해석될 수 있다. 첫째, 부곡지역보다 높은 지형에서 함양된 지하수가 심부로 순환하게 되면서, 퇴적암 또는 심부의 화강암과 물-암석 반응이 진행된다. 이때 퇴적층에 함유되어 있던 황산염 광물의 용해반응으로 지하수는 다량의 $SO_4$를 함유하게 된다. 둘째, 지하수가 계속 심부로 순환하는 과정에서 환원환경에 접하게 되어 $H_2$S가 생성되고, 심부열원에 의하여 약 13$0^{\circ}C$까지 가열되어 규산 염광물과의 반응정도가 높아진다. 이 때 pH는 상승하고 SO$_4$함량은 감소하게 되며, 방해석이 침전조건에 놓이게 됨으로써, 결국 지열수는 Na-SO$_4$형을 띠게 된다. 셋째, 이렇게 형성된 지열수가 유동로를 따라 상승하는 과정에서 덜 깊게 순환하는 지하수와 혼합과정을 거치게 된다. 지열수와 혼합되는 지하수는 퇴적층내 황철석의 산화반응에 의해 다량의 SO$_4$를 함유한 것으로 사료된다. 이렇게 형성된 지열수는 계속 상승하면서 천부환경의 지하수와 혼합되어 부곡지역내 다양한 지화학 특성을 보이는 지열수를 형성하게 된다.