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A numerical model for coupling between atomization and spray dynamics in liquid rocket thrust chambersThis paper describes a novel method of coupling the atomization and spray combustion processes encountered in coaxial injection elements of liquid rocket engine thrust chambers. This method is based on the Jet-Embedding technique in which the liquid jet core equations and the gas phase equations are solved separately. The liquid and gas phase solutions, however, are coupled through the boundary conditions at the interface between the phases. The computational grid for the gas phase calculations are adapted to the shape of the liquid jet core. The axial variation of droplet sizes are calculated using a stability analysis appropriate for the atomization regime of liquid jet breakup. The predictions of this method have been validated with experimental data on low speed water jets. Using this method, calculations are performed for the SSME fuel preburner single injector flow field. The results obtained are in good agreement with the predictions of the volume-of-fluid method.
Document ID
19920071533
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Giridharan, M. G.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Lee, J. G.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Krishnan, A.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Przekwas, A. J.
(CFD Research Corp. Huntsville, AL, United States)
Gross, Klaus
(NASA Marshall Space Flight Center Hunstville, AL, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 92-3768
Accession Number
92A54157
Funding Number(s)
CONTRACT_GRANT: NAS8-38425
Distribution Limits
Public
Copyright
Other

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