Les of supersonic combustion of H

A. Del Rossi, A. Ingenito, V. Parisi, C. Bruno, E. Giacomazzi

Research output: Contribution to conferencePaper

4 Citations (Scopus)

Abstract

The aim of this work is to numerically analyze supersonic combustion in a representative scramjet combustion geometry, focusing attention on turbulent mixing, flame stabilization and fuel conversion rate. The wind tunnel built at the University of Tokyo, consisting in a channel with a rectangular cross section and a step on the lower wall, followed by a divergent channel has been simulated. Hydrogen fuel is injected in cross-stream past the step and ahead of the divergent channel. Vitiated air enters the channel at Mach 2, P=49.7 kPa, T = 1145 K; hydrogen enters at Mach 1, P=171 kPa, T=248 K. In order to show the effect of different subgrid scale models on results, 3-D unsteady LES simulations have been simulated by using the Smagorinsky and FM models. The Smagorinsky model is coupled with the EDC model to treat turbulencecombustion interaction. Hydrogen oxidation is treated by means of a one-step global reaction. Numerical results point out no substantial differences by using the two models, and show a different flame anchoring mechanism with respect to that observed in the experiments.
Original languageEnglish
DOIs
Publication statusPublished - 2004
Event40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - , United States
Duration: 1 Jan 2004 → …

Conference

Conference40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
CountryUnited States
Period1/1/04 → …

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All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Del Rossi, A., Ingenito, A., Parisi, V., Bruno, C., & Giacomazzi, E. (2004). Les of supersonic combustion of H. Paper presented at 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, United States. https://doi.org/10.2514/6.2004-3877