3-D numerical investigation on supersonic combustion of hydrogen in two different type of scramjet combustors
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3-D numerical investigation on supersonic combustion of hydrogen in two different type of scramjet combustors
Vol. 23, Issue 3, (2008)
作者机构:
清华大学 航天航空学院,北京,100084
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Published:2008
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ZHOU Jian-xing, PIAO Ying, QI Xing-ming, et al. 3-D numerical investigation on supersonic combustion of hydrogen in two different type of scramjet combustors[J]. 2008, 23(3).
DOI:
ZHOU Jian-xing, PIAO Ying, QI Xing-ming, et al. 3-D numerical investigation on supersonic combustion of hydrogen in two different type of scramjet combustors[J]. 2008, 23(3).DOI:
3-D numerical investigation on supersonic combustion of hydrogen in two different type of scramjet combustors
The flow fields of hydrogen injected into combustors with step injectors and strut injectors were numerically investigated by solving the 3-Dcompressible Navier-Stokes and species equations with implicit finite volume method.The results show that because of the stronger streamwise and spanwise vortexes induced by the hydrogen flows injected via the strut injectors
hydrogen/air mixing efficiency is greatly enhanced and the mixing length along the channel is shortened.Besides
the cavities in both types of combustors enable the fuel to be mixed more fully and also stabilize the flame
enlarging the combustion area in the rear parts of the combustors.
3-D numerical investigation on supersonic hydrogen combustion in scramjet combustor
Numerical study on flow field in three supersonic combustors
Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow
Effect of turbulent combustion model on simulation of hydrogen supersonic combustion
Source term model of vane flow on a flat plate
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