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摘要
The reactive flow through a model scramjet combustor is simulated using a hybrid large-eddy/Reynolds-averaged Navier-Stokes technique. The scramjet configuration considered is similar to the one investigated at the Institute for Chemical Propulsion of the DLR, German Aerospace Center. The model scramjet consists of 15 fuel-injecting holes, located on the base of a wedge-shaped fuel injector, through which hydrogen is injected at sonic conditions. In the present study, only five of the 15 fuel-injecting holes are considered, and periodicity is assumed in the spanwise direction. Several parametric studies are conducted with a view toward determining the sensitivities of the predictions to modeling and algorithmic variations. Different grids (two different topologies), flux reconstruction methods (total variation diminishing and piecewise parabolic method), reaction mechanisms, and inflow boundary conditions (uniform and nonuniform) are used. To enhance fuel-air mixing, a synthetic eddy method is used to generate turbulence in the injector boundary layers and the hydrogen jets. Finally, a partially stirred reactor-type subgrid combustion model is used as a subgrid closure for the species production rates. The results show that, in all the cases, a lifted flame is predicted with varying standoff distances, heat releases, and shapes.
- 出版日期2014-7
