Journal of Astronautics ›› 2017, Vol. 38 ›› Issue (1): 80-88.doi: 10.3873/j.issn.1000-1328.2017.01.011

Previous Articles     Next Articles

Combustion Flow Field Analysis of a Scramjet Engine at High Mach Number

ZHANG Shi kong, LI Jiang, HUANG Zhi wei, QIN Fei, XUE Rui   

  1. Science and Technology on Combustion, Internal Flow and Thermo structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China
  • Received:2016-04-15 Revised:2016-11-07 Online:2017-01-15 Published:2017-01-25

Abstract:

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.

Key words: Scramjet, High Mach number, Combustion mode, Numerical simulation

CLC Number: