Experimental and simulation study of a Gaseous oxygen/Gaseous hydrogen vortex cooling thrust chamber

Experimental and simulation study of a Gaseous oxygen/Gaseous hydrogen vortex cooling thrust chamber

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Article ID: iaor201530069
Volume: 118
Start Page Number: 11
End Page Number: 20
Publication Date: Jan 2016
Journal: Acta Astronautica
Authors: , , ,
Keywords: design, simulation, experiment
Abstract:

In this paper, RNG k-ϵ turbulence model and PDF non-premixed combustion model are used to simulate the influence of the diameter of the ring of hydrogen injectors and oxidizer-to-fuel ratio on the specific impulse of the vortex cooling thrust chamber. The simulation results and the experimental tests of a 2000N Gaseous oxygen/Gaseous hydrogen vortex cooling thrust chamber reveal that the efficiency of the specific impulse improves significantly with increasing of the diameter of the ring of hydrogen injectors. Moreover, the optimum efficiency of the specific impulse is obtained when the oxidizer-to-fuel ratio is near the stoichiometric ratio.

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