Hybrid RANS/LES of a supersonic combustor
Hybrid RANS/LES of a supersonic combustor
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DOI:
10.2514/6.2008-6923
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发表时间:
2008
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影响因子:
--
通讯作者:
D. Peterson;G. Candler
中科院分区:
文献类型:
--
作者:
D. Peterson;G. Candler
Preliminary results from simulations modeling ush wall fuel injection in scramjet engines is presented. The simulations use a hybrid Reynolds-averaged Navier-Stokes and large eddy simulation methodology, where the primary function of the RANS mode is to act as a wall model for the large eddy simulation. The hybrid method is based on the delayed detached-eddy simulation formulation and includes improvements for functioning as a wall-modeled large eddy simulation. A seven species, eight reaction mechanism for hydrogen-air chemistry is coupled with the ow solver. The results presented here do not include the eects of subgrid turbulence-chemistry interaction. The instantaneous structure and ignition characteristics of a transverse jet of hydrogen in a supersonic crossow is compared to planar laser induced uorescence of OH radicals. The chemical mechanism used results in autoignition of the jet. The thin, wrinkled lament of OH observed in the experiment is reproduced well by the simulation. A model hydrogen-powered scramjet combustor for which there are internal measurements of temperature and species concentration, as well as wall pressure measurements, was also simulated. Well into the simulation a combustion front develops within the combustor that propagates upstream. As of the time this paper was written, the front is still moving upstream. The development of the combustion front it discussed and initial comparisons to the experimental data are made. The initial comparisons are promising, showing mean ow quantities that are qualitatively similar to what is measured experimentally.