Numerical Studies on the Mixing of CH4 and Kerosene Injected Into a Supersonic Flow With H2 Pilot Injection
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摘要: 用双流体模型和分区算法,气相多组分N-S方程和液相Euler方程分别用迎风TVD格式和NND格式进行数值求解,相间相互作用项方程用二阶Runge-Kutta法求解。并首次对H2引燃的CH4和煤油横向喷射、混合问题进行了数值研究。结果表明:与喷射加碘空气的PLIF结果相比,本文和实验结果符合得很好。对直通道,后面喷嘴的穿透深度大,煤油较气态燃料的穿透深度大,但难以被卷吸到喷嘴前的回流区内,流场出现无煤油区。H2和CH4均可扩散到回流区内,CH4和煤油引燃机理不同。对后台阶直通道,存在两个回流区,H2可扩散到这两个回流区,但CH4只能被卷吸到其喷嘴前的回流区。后台阶直通道增强混合的效果和引燃点火的可靠性更好。Abstract: Two-fluid model and divisional computation techniques were used.The multi-species gas fully N-S equations were solved by upwind TVD scheme.Liquid phase equations were solved by NND scheme.The phases-interaction ODE equations were solved by 2nd Runge-Kutta approach.The favorable agreement is obtained between computational results and PLIF experimental results of iodized air injected into a supersonic flow.Then,the numerical studies were carried out on the mixing of CH4 and kerosene injected into a supersonic flow with H2 pilot injection.The results indicate that the penetration of kerosene approaches maximum when it is injected from the second injector.But the kerosene is less diffused compared with the gas fuels.The droplet free region appears in the flow-field.The mixing mechanism of CH4 with H2 pilot injection is different from that of kerosene.In the staged duct,H2 can be entrained into both recirculation zones produced by the step and injectors.But CH4 can only be carried into the recirculation between the injectors.Therefore,initiations of H2 and CH4 can occur in those regions.The staged duct is better in enhancing mixing and initiation with H2 pilot flame.
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Key words:
- hydrocarbon fuels /
- supersonic flow /
- supersonic combustion /
- numerical simulation
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[1] Kay I W, Peschke W J,Guile R N. Hydrocarbon-fueled ramjet combustor investigation[A]. AIAA Paper, 90-2337, 1990. [2] Waltrup P J. Liquid fueled supersonic combustion ramjets. A research prospective of the past, present and future[A]. AIAA Paper. 86-0158, 1986. [3] Andrews E H, Trexler C A, Emami S. Tests of a fixed-geometry inlet-combustor configuration hydrocarbon-fueled, dual-mode scramjet[A]. AIAA Paper, 94-2817, 1994. [4] Billig F S. Supersonic combustion ramjet technology missile[J]. J Propulsion and Power, 1995,11(1): 1139-1146. [5] Narayanan A K, Damadaran K A. Experimental studies on piloted supersonic combustion using the petal nozzle[J]. J Propulsion and Power, 1997,13(1): 142-148. [6] Vinnogradov V A, Kobigsky S A, Petrov M D. Experimental investigation of kerosene fuel combustion in supersonic flow[J]. J Propulsion and Power,1995,11(1): 130-134. [7] Schetz J A, Kush E A, Joshi P B. Wave phenomena in liquid jet breakup in a supersonic cross-flow[J]. AIAA J, 1980,18(7): 774-778. [8] Less D M, Schetz J A. Transient behavior of liquid jets injected normal to a high velocity gas stream[J]. AIAA J, 1986, 24(12): 1979-1986. [9] Igra O, Ben-Dor G. Dusty shock waves[J]. Applied Mechanics Rev, 1988, 41(11): 397-437. [10] Yee H C, Klopeer G H, Montagne J L. High-resolution shock-capturing schemes for inviscid and viscous hypersonic flows[J]. J Comp Phys,1990,88: 31-66. [11] 张涵信,黎作武. 高超声速层流尾迹的数值模拟[J]. 力学学报,1992, 24(4): 389-399. [12] McDaniel J C, Graves J, Jr. A laser-induced fluorescence visualization study of transverse, sonic fuel injection in a non-reacting supersonic combustor[A]. AIAA Paper, 86-0507,1986. [13] Uenishi K, Rogers R C. Three-dimensional computational of mixing of transverse injector in a ducted supersonic airstream[A]. AIAA Paper,86-1423,1986. -
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