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The 3D rocket combustor acoustics modelThe theory and procedures for determining the characteristics of pressure oscillations in rocket engines with prescribed burning rate oscillations are presented. Analyses including radial and hub baffles and absorbers can be performed in one, two, and three dimensions. Pressure and velocity oscillations calculated using this procedure are presented for the SSME to show the influence of baffles and absorbers on the burning rate oscillations required to achieve neutral stability. Comparisons are made between the results obtained utilizing 1-D, 2-D, and 3-D assumptions with regards to capturing the physical phenomena of interest and computational requirements.
Document ID
19920017792
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Priem, Richard J. (Priem Consultants, Inc., Cleveland OH., United States)
Breisacher, Kevin J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:105734
E-7137
AIAA PAPER 92-3228
NASA-TM-105734
Report Number: NAS 1.15:105734
Report Number: E-7137
Report Number: AIAA PAPER 92-3228
Report Number: NASA-TM-105734
Meeting Information
Meeting: Joint Propulsion Conference and Exhibit
Location: Nashville, TN
Country: United States
Start Date: July 6, 1992
End Date: July 8, 1992
Sponsors: SAE, ASME, ASEE, AIAA
Accession Number
92N27035
Funding Number(s)
PROJECT: RTOP 590-21-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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