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학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
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- 2018
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Flow mixing and flame characteristics of the RCM-3 rocket injectors operating at supercritical pressures have been studied numerically. Combination of fuel and oxidizer, momentum flux ratio, and recess ratio are important parameters in understanding combustion characteristics of the non-premixed combustion. Therefore, to investigate the relationship between flow mixing and flame characteristics, we select eight momentum flux ratios for hydrogen-oxygen, five momentum flux ratios for methane-oxygen, and five recess ratios in the Mascotte combustor configuration. The turbulence model and combustion model are based on the modified standard k-e and steady flamelet Model. The result shows a sequence of three recirculating flow depending on the generation position of pseudo boiling, and shows a change in flame structure. Regardless of the type of fuel, three type flames are generated for J<4.15 (A-type), 8.47<J<38.5 (B-type), J>46.1 (C-type). For the variation of the recess ratio, B-type flame is observed at the recess ratio of 1.0 and 1.5, and for the larger recess ratio, the flame becomes C-type. The B-type flame gives a shorter flame length and a radially spreaded shape due to the central recirculation flow.
In order to find similar characteristics for the flow changes by recess length and swirl inlet, the swirl velocity with the oxygen inlet is explored. According to the swirl intensity, A-type and B-type flames are only generated, and B-type flame has an excellent combustion efficiency. The shortest mixing length of RR=1.5 corresponds to that of S=5.67
In order to find similar characteristics for the flow changes by recess length and swirl inlet, the swirl velocity with the oxygen inlet is explored. According to the swirl intensity, A-type and B-type flames are only generated, and B-type flame has an excellent combustion efficiency. The shortest mixing length of RR=1.5 corresponds to that of S=5.67
목차
Ⅰ. Introduction 1Ⅱ. Numerical Methods 52.1 Governing Equation 52.1.1 Governing Equation of Fluid Flow 52.1.2 Equation of State 52.1.3 Turbulence Model 62.1.4 Combustion Model 72.2 Computational Domain 92.2.1 Mascotte Rocket Combustor 92.3 Operating Condition 102.3.1 RCM-3 Test Case (Gas Hydrogen - Liquid Oxygen) 102.3.2 G2 Test Case (Gas Methane - Liquid Oxygen) 112.4 Numerical Methods 122.5 Validation 122.5.1 Validation of Numerical Methods 122.5.2 Grid Dependency 17Ⅲ. Results and Discussion 183.1 Pseudo boiling effect 183.2 Effects of Momentum Flux Ratios 203.3 Effects of Recess Lengths 243.4 Effects of Swirl Intensity 30Ⅳ. Conclusions 33Reference 35Abstract 39
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