Combustion flow field analysis of a scramjet engine at high Mach number

被引：0
|
作者：
Zhang S.-K. [1 ]
Li J. [1 ]
Huang Z.-W. [1 ]
Qin F. [1 ]
Xue R. [1 ]
机构：
[1] Science and Technology on Combustion, Internal Flow and Thermo-structure Laboratory, Northwestern Polytechnical University, Xi'an
来源：
| 2017年 / China Spaceflight Society卷 / 38期
关键词：
Combustion mode; High Mach number; Numerical simulation; Scramjet;
D O I：
10.3873/j.issn.1000-1328.2017.01.011
中图分类号：
学科分类号：
摘要：
A hydrogen-fueled ground testing scramjet engine operating at flight Ma 12 is numerically studied. Computation of the combustion field is carried out based on the commercial software CFD++. The basic flow structure, the spatial distribution of heat release, the combustion mode of premixed/non-premixed, and the mechanism of flame stabilization of the scramjet engine which works at Ma 12 are investigated in detail. A hydrogen-air chemistry kinetic model consisting of 7 species, 9 reaction steps is adopted in the Reynolds-Averaged Navier-Stokes simulation. The two-equation shear-stress-transport(SST) turbulence model which takes account of the wall functions is used to handle the turbulence-chemistry interactions. The results are validated by the experimentally measured wall pressure distribution with good agreement. 1) The applicability and accuracy of CFD++ in the study of compressible reactive flows under high flight Mach numbers are verified; 2)the combustion characteristics under hypersonic inflow conditions are studied; 3) the combustion efficiency, the heat release, and the combustion mode are obtained for the very high Mach number; 4)these observations offer insight into the potential for exploring the mechanisms of the combustion simulation and multi-scale combustion dynamics under hypersonic flow conditions. © 2017, Editorial Dept. of JA. All right reserved.
引用
收藏
页码：80 / 88
页数：8
相关论文
共 24 条
  • [1] Qin F., He G.-Q., Liu P.-J., Et al., Numerical simulation of strut-rocket scramjet with circular combustor, Journal of Solid Rocket Technology, 34, 2, pp. 150-155, (2011)
  • [2] Yu G., Fan X.-J., Supersonic combustion and hypersonic propulsion, Adv. Mech., 43, 5, pp. 449-471, (2013)
  • [3] Erik A., Ajay K., Alan W., Study of forebody injection and mixing with application to hypervelocity air breathing propulsion, 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, (2012)
  • [4] Heiser W., Pratt D., Daley D., Et al., Hypersonic Airbreathing Propulsion, (1994)
  • [5] Huang W., Luo S.-B., Wang Z.-G., Key techniques and prospect of near-space hypersonic vehicle, Journal of Astronatics, 31, 5, pp. 1259-1265, (2010)
  • [6] Rogers R.C., Shih A.T., Hass N.E., S cramjet development tests supporting the Mach 10 flight of the X-43, AIAA/CIRA 13th International Space Planes and Hypersonic Systems and Technologies, (2005)
  • [7] Mathew G.B., Laurie M.B., Russell R.B., Supersonic combustion processes in a premixed three-dimensional nonuniform compression scramjet engine, AIAA Journal, 52, 8, pp. 1670-1684, (2014)
  • [8] Masatoshi K., Vigor Y., Masahiro T., Et al., Ignition transient phenomena in a scramjet engine at Mach 12 flight condition, 43rd AIAA/ASME/SAE/SAEE Joint Propulsion Conference & Exhibit, (2007)
  • [9] Zhou J.-X., Wang Y., Numerical investigation on performance of a high Mach number scramjet, Journal of Propulsion Technology, 35, 4, pp. 433-441, (2014)
  • [10] Wang P.-Y., Chen M., Xing F., Et al., CFD numerical simulation of hyshot scramjet, Journal of Aerospace Power, 29, 5, pp. 1021-1023, (2014)
123