Numerical simulation of a scramjet combustion chamber

E. Giacomazzi, A. Del Rossi, C. Bruno

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Abstract

A typical operation mode for SCRJ engines consists in injecting fuel into a cross-flowing supersonic air stream. In this paper we numerically simulate a sonic H2 jet injected into cross-flowing vitiated air stream at Mach 2 focusing on mixing and flame stabilization. We simulate both reactive and nonreactive flows in 3-D with a commercial code by using RANS and LES techniques. We also investigate the effect of preheating the fuel, and, preliminarily, the influence of eddy viscosity on mixing and fuel conversion. Results indicate that fuel preheating up to 1200 K is insufficient to ensure stable flame anchoring in the presence of inadequate mixing. A simple criterion is proposed to size fuel injection geometry and kinematics. Copyright © 2003 by the International Astronautical Federation. All rights reserved.

Conference

Conference54th International Astronautical Congress of the International Astronautical Federation (IAF), the International Academy of Astronautics and the International Institute of Space Law
CountryGermany
Period1/1/03 → …

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All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Giacomazzi, E., Del Rossi, A., & Bruno, C. (2003). Numerical simulation of a scramjet combustion chamber. Paper presented at 54th International Astronautical Congress of the International Astronautical Federation (IAF), the International Academy of Astronautics and the International Institute of Space Law, Germany.