CFD numerical simulation of Hyshot scramjet
-
摘要: 以Hyshot超燃冲压发动机试验为研究对象,分别对冷流和燃烧工况进行了CFD数值模拟.冷流模拟计算得到的壁面压力与试验结果吻合良好,且数值计算压力分布对采用的湍流流动模型不敏感;但是采用不同的湍流流动模型计算的湍流参数(湍动能和耗散率)差别很大,会对氢气燃料与气流的掺混产生重要影响,进而影响燃烧模拟结果.采用SST(shear stress transport)k-ω湍流流动模型和EDM(eddy dissipation model)湍流燃烧模型得到的模拟结果与试验结果基本吻合,但是计算压力峰值略靠后.对8个不同氢气燃料喷射角度的工况进行数值模拟结果表明喷射角度为99°和114°时燃料和空气混合最好、燃烧效率可达到最高.Abstract: CFD numerical simulation was carried out for cold flow and combustion flow of the Hyshot scramjet to test the accuracy of turbulence flow model and turbulent combustion model. For cold flow, the predicted wall pressure profile was in accurate agreement with experimental data and the simulation result was insensitive to turbulence flow model choice. However, the predicted field of turbulence variables (turbulence kinetic energy and its dissipation rate) in cold flow is strongly influenced by turbulence flow model choice; these turbulence variables affect the mixing of hydrogen fuel and air and the subsequent combustion. Indeed, the simulation of combustion flow showed strong dependence on turbulence flow model and turbulent combustion model choice. The best combustion simulation result with SST k-ω turbulence flow model and EDM turbulence combustion model has good agreement with experimental wall pressure data, but the pressure peak location is slightly deviated. The effect of fuel injection angle was also simulated. Eight injection angles of hydrogen fuel were tested and it was shown that the scramjet has best fuel/air mixing and combustion efficiency with injection angles of 99° and 114°.
-
[1] 科林·西格尔.超燃冲压发动机:过程和特性[M].张新国, 译.北京:航空工业出版社, 2009. [2] Curran E T, Heiser W H, Pratt D T.Fluid phenomena in scramjet combustion systems[J].Annual Review of Fluid Mechanics, 1996, 28:323-360. [3] Heiser W H, Pratt D T.Hypersonic airbreathing propulsion[M].Washington:AIAA Education Series, 1994. [4] Odam J.Scramjet experiments using radical farming[D].Brisbane, Australia:The University of Queensland, 2004. [5] Mudford N, Mulreany P.CFD calculation for intake-injection shock-induced combustion scramjet flight experiments[R].AIAA-2003-7034, 2003. [6] Fureby C, Chapuis M.CFD analysis of the Hyshot Ⅱ scramjet combustor[J].Proceedings of the Combustion Institute, 2011, 33(2):2399-2405. [7] Rubins P M, Rhodes R P Jr.Shock-induced combustion with oblique shocks, comparison of experiment and kinetic calculations[J].AIAA Journal, 1963, 1(12):2778-2784. [8] Mudford N R, Mulreany P J, McGuire J R, et al.CFD calculations for intake-injection shock-induced-combustion scramjet flight experiments[R].AIAA-2003-7034, 2003. [9] Odam J, Paull A.Radical farming in scramjets[J].Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 2007, 96:276-283. [10] Brindle A, Boyce R R, Neely A J.CFD analysis of an ethylene-fueled intake-injection shock-induced-combustion scramjet configuration[R].AIAA-2005-3239, 2005. [11] Wilcox D.Turbulence modeling for CFD[M].3rd ed.La Canada Flintridge, CA:DCW Industries, 2006. [12] Magnussen B, Hjertager B.On mathematical modeling of turbulent combustion with special emphasis on soot formation and combustion[J].Symposium (International) on Combustion, 1977, 16(1):719-729. [13] 王培勇, 汪延鹏, 冯韬, 等.涡团耗散模型A值对模拟精度的影响[R].重庆:工程热物理学会燃烧学年会, 2013. [14] 林志勇.高静温超声速预混气爆震与发展过程机理研究[D].长沙:国防科学技术大学, 2008. LIN Zhiyong.Research on detonation initiation and development mechanisms in elevated temperature supersonic premixed mixture[D].Changsha:National University of Defense Technology, 2008.(in Chinese) [15] Star J, Edwards J, Smart M, et al.Numerical simulation of scramjet combustion in a shock tunnel[R].AIAA-2005-0428, 2005. [16] Gardner A.Upstream porthole injection in a 2-D scramjet model[J].Shock Waves, 2002, 11(5):369-375.
点击查看大图
计量
- 文章访问数: 1754
- HTML浏览量: 0
- PDF量: 1033
- 被引次数: 0