Influence of fuel injection position and equivalent mixture ratio on chemical non-equilibrium effects of single expansion ramp nozzle
Influence of fuel injection position and equivalent mixture ratio on chemical non-equilibrium effects of single expansion ramp nozzle
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摘要: Chemical non-equilibrium flow was investigated for the scramjet single expansion ramp nozzle(SERN) with a strut-based liquid-kerosene-fueled combustor.Two-dimensional Reynolds-averaged Navier-Stokes(RANS) equations were solved with the species conservation equation for continuous phase and the renormalization group(RNG) k-ε turbulence model.Lagrangian discrete-phase model was analyzed for liquid-kerosene droplets behavior in the supersonic stream.Combustion was simulated by kerosene surrogate fuel's 10-species and 13-step reduced reaction kinetics mechanism with use of Arrhenius's laminar finite rate model.Parametric studies were carried out to estimate the influence of different fuel injection positions and equivalent mixture ratios on the SERN chemical non-equilibrium effects.Numerical calculation results show that the strut-based combustor enables convenient modeling of various SERN entry conditions,which is similar with many preceding investigations,by changing the injector strut position and controlling the mass flow rate of each injector.Chemical non-equilibrium effects function in the whole SERN,especially in the initial flow expansion region,leads to obviously higher SERN performance of the non-equilibrium flow than that of the frozen flow.Furthermore,the distributed fuel injection pattern plays a significant role in enhancing the combustion efficiency in combustor,but weakening the chemical non-equilibrium effects funciton in SERN.Additionally,while the equivalent mixture ratio increases,the SERN thrust coefficient and lift coefficient rise gradually,and the increment of non-equilibrium flow in relation to frozen flow becomes higher as well.To be specific,the equivalent mixture ratio is 0.6,the maximum increment of thrust coefficient and lift coefficient are 11.6% and 25% respectively.Abstract: Chemical non-equilibrium flow was investigated for the scramjet single expansion ramp nozzle(SERN) with a strut-based liquid-kerosene-fueled combustor.Two-dimensional Reynolds-averaged Navier-Stokes(RANS) equations were solved with the species conservation equation for continuous phase and the renormalization group(RNG) k-ε turbulence model.Lagrangian discrete-phase model was analyzed for liquid-kerosene droplets behavior in the supersonic stream.Combustion was simulated by kerosene surrogate fuel's 10-species and 13-step reduced reaction kinetics mechanism with use of Arrhenius's laminar finite rate model.Parametric studies were carried out to estimate the influence of different fuel injection positions and equivalent mixture ratios on the SERN chemical non-equilibrium effects.Numerical calculation results show that the strut-based combustor enables convenient modeling of various SERN entry conditions,which is similar with many preceding investigations,by changing the injector strut position and controlling the mass flow rate of each injector.Chemical non-equilibrium effects function in the whole SERN,especially in the initial flow expansion region,leads to obviously higher SERN performance of the non-equilibrium flow than that of the frozen flow.Furthermore,the distributed fuel injection pattern plays a significant role in enhancing the combustion efficiency in combustor,but weakening the chemical non-equilibrium effects funciton in SERN.Additionally,while the equivalent mixture ratio increases,the SERN thrust coefficient and lift coefficient rise gradually,and the increment of non-equilibrium flow in relation to frozen flow becomes higher as well.To be specific,the equivalent mixture ratio is 0.6,the maximum increment of thrust coefficient and lift coefficient are 11.6% and 25% respectively.
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[1] Kumaran K,Babu V.Mixing and combustion characteristics of kerosene in a model supersonic combustor[J].Journal of Propulsion and Power,2009,25(3):583-592. [2] YU Yong,DING Meng,LIU Weidong,et al.Experimental study of supersonic combustion of kerosene[J].Journal of National University of Defense Technology,2004,26(1):1-4.(in Chinese) [3] Yu G,Li J G,Chang X Y,et al.Investigation of kerosene combustion characteristics with pilot hydrogen in model supersonic combustor[J].Journal of Propulsion and Power,2001,17(6):1263-1272. [4] WANG Xinyue,YANG Zhenpeng,WANG Yanqing.Effects of non-equilibrium chemical reaction flow on the performance of scramjet nozzle[J].Journal of Aerospace Power,2009,24(5):1022-1027.(in Chinese) [5] Thomas L,Wolfgang W K.Computation of a nonequilibrium expansion flow in a single expansion ramp nozzle[J].Journal of Propulsion and Power,2001,17(6):1353-1360. [6] Kaneko M,Menshov I,Nakamuka Y.Numerical simulation of non-equilibrium flow in high-enthalpy shock tunnel with EIH scheme[R].AIAA-2001-2860,2001. [7] Manna P,Behera R,Chakraborty D.Liquid-fueled strut-based scramjet combustor design:a computational fluid dynamics approach[J].Journal of Propulsion and Power,2008,24(2):274-281. [8] Malo-Molina F J,Gaitonde D V,Ebrahimi H B.Numerical investigation of a 3D chemically reacting scramjet engine at high altitudes using JP8-air mixtures[R].AIAA-2005-1435,2005. [9] Rajasekaran A,Babu V.Evaluation of a ramp cavity based concept supersonic combustor using CFD[J].Progress in Computational Fluid Dynamics,2009,9(1):16-19. [10] Baurle R A,Eklund D R.Analysis of dual-mode hydrocarbon scramjet operation at Mach 4—6.5[J].Journal of Propulsion and Power,2002,18(5):990-1002. [11] Christopher R,Joseph A S.Experimental and numerical studies of a strut injector for round scramjet combustors.AIAA-2009-7313,2009. [12] Marius C B,Tobias S,Jaechul C,et al.Numerical study of supersonic combustion processes with central strut injection[J].Journal of Propulsion and Power,2010,26(4):869-874. [13] Kumaran K,Behera P R,Bahu V.Numerical investigation of the supersonic combustion of kerosene in a strut-based combustor[J].Journal of Propulsion and Power,2010,26(5):1084-1091. [14] Ramya P H,Marathe A G.A computational study on supersonic combustion with struts as flame holder[R].AIAA-2008-4712,2008. [15] Rajasekaran A,Satishkumar G,Babu V.Numerical simulation of the supersonic combustion of kerosene in a model combustor[J].Progress in Computational Fluid Dynamics,2009,9(1):30-42. [16] ZHOU Zheng,NI Hongli,HE Xuzhao,et al.Optimization design of single expansion ramp nozzle based on Rao's method[J].Journal of Propulsion Technology,2009,30(4):451-456.(in Chinese) [17] LIU Ouzi,CAI Yuanhu,HU Yuli,et al.The turbulence models for numerical analysis of liquid kerosene supersonic combustion[J].Acta Aerodynamica Sinica,2007,25(3):362-367.(in Chinese) [18] Amsden A A.KIVA-Ⅲ:a KIVA program with block structure mesh for complex geometry[R].LA-12503-MS,1993. [19] HUANG Shenghong,XU Shengli,LIU Xiaoyong.Combustion flow of kerosene-fueled scramjet with 3D cavity:Ⅲ[J].Journal of Propulsion Technology,2005,26(2):101-105.(in Chinese) [20] Ten-See W.Thermophysics characterization of kerosene combustion[J].Journal of Thermophysics and Heat Transfer,2001,15(2):140-147. [21] Kundu K P,Penko P F,Yang S L.Simplified jet-A/air combustion mechanisms for calculation of NOx emissions.AIAA 98-3986,1998. [22] Arbor A.FLUENT 6.3 User's Guide[M]. :Ansys Incorporation,2006. [23] WU Xianyu.Research on design and optimization of integrated scramjet flowpath[D].Changsha:National University of Defense Technology,2007.(in Chinese) [24] Pierce M,Ely W.A computational exploration of the importance of three-dimensionality,boundary layer development,and flow chemistry to the prediction of scramjet nozzle forces and moments[R].AIAA 91-5059,1991. [25] LIU Ouzi,CAI Yuanhu,HU Yuli,et al.Experimental investigation of kerosene fuel combustion in the supersonic flow[J].Journal of Propulsion Technology,2005,26(3):276-279.(in Chinese) -
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