超音速燃燒流場一般極為複雜，主要有震波與邊界層之間的相互影響，還有在高速氣流下燃料跟氧化劑的混合現象與燃燒反應。因此，本論文建立一套可分析超音速燃燒流場的數值模式。本研究的探討參數方面，包含了不同紊流模式對於超音速流場的預測精準度，紊流模式包括了SST k-ω與RNG k-ε。並進一步分析燃燒室維度上的差異與兩組不同的氫氧反應式對燃燒流場的影響。燃燒化學模型採用Flamelet模型。模擬結果說明，在深度很小的燃燒室流場中，三維效應劇烈，不可輕易忽略。反應式的不同在相同紊流模式下並無劇烈的影響性，只有在局部溫度上有些微差異。紊流模式方面，SST k-ω的模擬結果也都比RNG k-ε更為接近實驗值。綜合以上，本論文模擬成果發現SST k-ω搭配Jachimowski(2006) 所提出的32條氫氧反應式在分析超音速燃燒流場與Oevermann(2000)等人過去的計算文獻相較之下有較佳的準確性。

General supersonic flow field is complex, due to the mixing and combustion of the injected fuel in the high-speed flow and the interaction between the shock wave and the boundary layer. Therefore, the numerical model for the supersonic flow has been established in the present study. The effect of turbulence models, i.e., the SST-k-ω and RNG-k-ε turbulence model, on the prediction of the supersonic flow has been investigated. The effects of employed dimension and hydrogen-oxygen combustion model on the combustion flow field have also been investigated. The Flamelet model is employed for the chemical combustion. The simulation results indicate that the effect of three-dimension on the small depth combustor is significant. The effect of employed reaction model on the supersonic combustion is not significant, resulting in minor difference of the local temperature. The simulation results also indicate that the SST-k-ω turbulence model is superior to the RNG k-ε turbulence model in predicting the characteristics of supersonic flow. The simulation results also show that the SST k-ω model combining with the 32 hydrogen-oxygen reactions model proposed by Jachimowski(2006) leads to better accuracy than that of Oevermann(2000) et al. in the prediction of the supersonic combustion.

[1]Waidmann, W and Brummund, U., “Supersonic Combustion of Hydrogen/Air in a Scramjet Combustion Chamber”, Space Technol, Vol.15, NO.6, pp.421-429, 1995.
[2]Guerra, R and Waidmann, W, “An Experimental Investigation of the Combustion of a Hydrogen Jet Injected Parallel in a Supersonic Air Stream”, AIAA-91-52, 1991.
[3]Kumaran, K and Babu, V., “Investigation of the Effect of Chemistry Model on the Numerical Predictions of the Supersonic Combustion of Hydrogen”, Combustion and Flame, January 2009.
[4]Oevermann, M., “Numerical Investigation of Turbulent Hydrogen Combustion in a Scramjet Using Flamelet modeling”, Aerospace Science and Technology, Vol.4, pp463-480, 2000.
[5]Ali, M., Fujiwara, T., and Leblanc, J.E., “Influence of Main Flow Inlet Configuration on Mixing and Flameholding in Transverse Injection into Supersonic Airstream”, International Journal of Engineering Science, Vol.38, pp.1161-1180, 2000.
[6]Ali, M., Islam, A.K.M-S., and Ahmed, S., “Mixing and Flame Holding with Air Inlet Configuration in Scramjet Combustor”, International Journal of Heat and Mass Tensfer, Vol.31, pp.1187-1198, 2004.
[7]Ali, M., and Islam, A.K.M.-S., “Study on Main Flow and Fuel Injector Confiqurations for Scramjet Applications”, International Journal of Heat and Mass Tensfer, Vol.49, pp.3634-3644, 2006.
[8]Rajasekaran, A and Babu, V., “Numerical Simulation of Three-Dimension Reacting Flow in a Model Supersonic Combustor”, Journal of Propulsion and Power, Vol.22, NO.4, July-August 2006.
[9]Aso, S., Okuyama, S., Kawai, M., and Ando, Y., “Experiment Study on Mixing Phenomena in Supersonic Flows with Slot Injection,”AIAA Paper 1991-0016, 1991.
[10]Rizzeta, D., “Numerical Simulation of Slot Injection into a Turbulent Supersonic Stream,”AIAA Paper 1992-0827, 1992.
[11]Chenault, C.F and Beran, P.S., “K- and Reynolds Stress Turbulence Model Comparisons for Two-Dimensional Injection Flows,”AIAA Journal, Vol. 36, No. 8, August 1998.
[12]Menter, F. R., “Two Equation Eddy-Viscosity Turbulence Models for Engineering Applications”, AIAA Journal, Vol.32, NO.8, August 1994.
[13]Wepler, U., and Koschel, W., “Numerical Investigation of Turbulent Reacting Flows in a Scramjet Combustor Model”, AIAA Paper 2002-3572, 2002.
[14]Alexander, D. C and Siislian, J. P., “Computational Study of the Propulsive Characteristics of a Shcramjet Engine”, Journal of Propulsion and Power, Vol.24, No.1, January-February 2008.
[15]Bartosiewicz, Y., Aidoun, Z., Desevaux, P., and Mercadier, Y., “Numerical and Experiment Investigation on Supersonic Ejector”, International Journal of Heat and Fluid Flow, Vol. 26, pp.56-70, 2005.
[16]Choi, J.Y., Ma, F., and Yang, V., “Combustion Oscillations in a Scramjet Engine Combustor with Transverse Fuel Injection”, Proceedings of the Combustion Institute, Vol.30, pp.2851-2858, 2005.
[17]Jeung, I.S and Choi, J.Y., “Numerical Simulation of Supersonic Combustion for Hypersonic Propulsion”, 5th Asia-Pacific Conference on Combustion, July 2005.
[18]Takahashi, S and Wakai, K., “Effect of Combustion on Flowfield in a Model Scramjet Combustor”, Combustion Institute, pp.2143-2150, 1998.
[19]Smark, M.K., “Flight Data Analysis of the Hyshot 2 Scramjet Flight Experiment”, AIAA Journal, Vol.44, No.10, October, 2006.
[20]Gardner, A. D and Paull, A., “Post Flight Analysis of the Hyshot Supersonic Combustion Flight Experiment in HEG ”, Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehcies, 8-11 November 2005, Cologen, Germany.
[21]Ho, S. K., “Coupled Thermal, Structural and Vibrational Analysis of a Hypersonic Engine for Flight Test”, Aerospace Science and Technology, pp.420-426, 2006.
[22]Doolan, C. J., “Hypersonic Missile Performance and Sensitivity Analysis”, Journal of Spacecraft and Rockets, Vol. 44, No. 1, January–February 2007.
[23]Takita, K and Murakaim, K., “A Novel Design of a Plasma Jet Torch Igniter in a Scramjet Combustor”, Proceedings of the Combustion Institute 30, pp. 2843–2849, 2005.
[24]Takita, K., “Ignition Enhancement by Addition of NO and NO2 from a N2/O2 Plasma Torch in a Supersonic Flow”, Proceedings of the Combustion Institute 31, pp. 2489–2496, 2007.
[25]Mitani, T., “Flame Structures and Combustion Efficiency Computed for a Mach 6 Scramjet Engine”, Combustion and Flame 142, pp.187–196, 2005.
[26]Draper, S. L., “Development and Evaluation of TiAl Sheet Structures for Hypersonic Applications”, Materials Science and Engineering A 464, pp. 330–342, 2007.
[27]Berglund, M and Fureby, C., “ LES of Supersonic Combustion in a Scramjet Engine Model”, Proceedings of the Combustion Institute 31, pp. 2497–2504,2007.
[28]Kei, Y. L., “Hypersonic Boundary-Layer Transition: Application to High-Speed Vehicle Design”, Journal of Spacecraft and Rockets, Vol. 45, No. 2, March–April 2008.
[29]Polivanov, P. A., “Numerical Simulation of Shock Wave/Turbulent Boundary Layer Interaction Using Fluent 6.3”, International Conference on Methods of Aerophysical Research, ICMAR 2008.
[30]Tabet, F., “Hydrogen-Hydrocarbon Turbulent Non-Premixed Flame Structure”, International Journal of Hydrogen Energy 34, pp.5040-5047, 2009.
[31]Amati, V., Bruno, C., Simone, D., and Sciubba, E., “Exergy Analysis of Hypersonic Propulsion System： Performance Comparison of Two Different Scramjet Configurations at Cruise Conditions”, Energy, Vol.33, pp.116-129, 2008.
[32]Tetlow, M. R and Doolan, C. J., “Comparison of Hydrogen and Hydrocarbon-Fueled Scramjet Engine for Oribital Insertion”, Journal of Spacecraft and Rockets, Vol.44, No.2, March-April 2007.
[33]Manna, P., Behera, R., and Chakraborty, D., “Liquid-Fueled Strut-Based Scramjet Combustor Design: A Computational Fluid Dynamics Approach”, Journal of Propulsion and Power, Vol.24, No.2, March-April 2008.
[34]Tomioka, S., Murakami, A., Kudo, K., and Mitani, T., “Combustion Tests of a Staged Supersonic Combustor with a Strut”, Journal of Propulsion and Power, Vol.17, NO.2, March-April 2001.
[35]Tomioka, S., Murakami, A., Kudo, K., and Mitani, T., “Effect oF Injection Configuration on Performance of a Staged Supersonic Combustor”, Journal of Propulsion and Power, Vol.19, NO.5, September-October 2003.
[36]Xianyu, W., Xiaoshan, L., Meng, D., Weidong, L., and Zhenguo, W., “Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance”, Chinese Journal of Aeronautics, Vol.20, pp.488-494, 2007.
[37]Gerlinger, P., Stoll, P., Kindler, M., Schneider, F., and Aigner, M., “Numerical Investigation of Mixing and Combustion Enhancement in Supersonic Combustors by Strut Induced”, Aerospace Science and Technology, Vol.12, pp.159-168, 2008.
[38]Rasmussen, C.C., Driscoll, J.F., Hsu, K.Y., Donbar, J.M., Gruber, M.R., and Carter, C.D., “Stability Limits of Cavity-Stabilized Flames in Supersonic Flow”, Proceedings of the Combustion Institute, Vol.30, pp. 2825-2833, 2005.
[39]Kim, K.-M., Beak, S.-W., and Han, C.-Y., “Numerical Study on Supersonic Combustion with Cavity-Based Fuel Injection”, International of Journal of Heat and Mass Transfer, Vol.47, pp.271-286, 2004.
[40]FLUENT 6.3 User’s Guide , 2006.
[41]Anderson, J.D., “Hypersonic and High-Temperature Gas Dynamics”, 2006.
[42]Chemkin Collection 3.7 User’s Guide, 2002.