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Comprehensive modeling of a liquid rocket combustion chamberAn analytical model for the simulation of detailed three-phase combustion flows inside a liquid rocket combustion chamber is presented. The three phases involved are: a multispecies gaseous phase, an incompressible liquid phase, and a particulate droplet phase. The gas and liquid phases are continuum described in an Eulerian fashion. A two-phase solution capability for these continuum media is obtained through a marriage of the Implicit Continuous Eulerian (ICE) technique and the fractional Volume of Fluid (VOF) free surface description method. On the other hand, the particulate phase is given a discrete treatment and described in a Lagrangian fashion. All three phases are hence treated rigorously. Semi-empirical physical models are used to describe all interphase coupling terms as well as the chemistry among gaseous components. Sample calculations using the model are given. The results show promising application to truly comprehensive modeling of complex liquid-fueled engine systems.
Document ID
19850037649
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Liang, P.-Y.
(Rockwell International Corp. Canoga Park, CA, United States)
Fisher, S.
(Rockwell International Corp. Canoga Park, CA, United States)
Chang, Y. M.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 85-0232
Accession Number
85A19800
Funding Number(s)
CONTRACT_GRANT: NAS8-34928
Distribution Limits
Public
Copyright
Other

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