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Ignition and combustion characteristics of metallized propellantsDuring this reporting period, theoretical work on the secondary atomization process was continued and the experimental apparatus was improved. A one-dimensional model of a rocket combustor, incorporating multiple droplet size classes, slurry combustion, secondary atomization, radiation heat transfer, and two-phase slip between slurry droplets and the gas flow was derived and a computer code was written to implement this model. The STANJAN chemical equilibrium solver was coupled with this code to yield gas temperature, density, and composition as functions of axial location. Preliminary results indicate that the model is performing correctly, given current model assumptions. Radiation heat transfer in the combustion chamber is treated as an optically-thick participating media problem requiring a solution of the radiative transfer equation. A cylindrical P sub 1 approximation was employed to yield an analytical expression for chamber-wall heat flux at each axial location. The code exercised to determine the effects of secondary atomization intensity, defined as the number of secondary drops produced per initial drop, on chamber burnout distance and final Al2O3 agglomerate diameter. These results indicate that only weak secondary atomization is required to significantly reduce these two parameters. Stronger atomization intensities were found to yield decreasing marginal benefits. The experimental apparatus was improved to reduce building vibration effects on the optical system alignment. This was accomplished by mounting the burner and the transmitting/receiving optics on a single frame supported by vibration-isolation legs. Calibration and shakedown tests indicate that vibration problems were eliminated and that the system is performing correctly.
Document ID
19920024323
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mueller, D. C. (Pennsylvania State Univ. University Park, PA, United States)
Turns, Stephen R. (Pennsylvania State Univ. University Park, PA, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Subject Category
Propellants And Fuels
Report/Patent Number
NASA-CR-190613
PSU-TR-92-010
NAS 1.26:190613
Accession Number
92N33567
Funding Number(s)
CONTRACT_GRANT: NAG3-1044
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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