NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Analysis of combustion instability in liquid propellant engines with or without acoustic cavitiesAnalytical studies have been made of the relative combustion stability of various propellant combinations when used with hardware configurations representative of current design practices and with or without acoustic cavities. Two combustion instability models, a Priem-type model and a modification of the Northern Research and Engineering (NREC) instability model, were used to predict the variation in engine stability with changes in operating conditions, hardware characteristics or propellant combination, exclusive of acoustic cavity effects. The NREC model was developed for turbojet engines but is applicable to liquid propellant engines. A steady-state combustion model was used to predict the needed input for the instability models. In addition, preliminary development was completed on a new model to predict the influence of an acoustic cavity with specific allowance for the effects the nozzle, steady flow and combustion.
Document ID
19740023268
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Oberg, C. L. (Rockwell International Corp. Canoga Park, CA, United States)
Kesselring, R. C. (Rockwell International Corp. Canoga Park, CA, United States)
Warner, C., III (Rockwell International Corp. Canoga Park, CA, United States)
Schuman, M. D. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1974
Subject Category
Thermodynamics And Combustion
Report/Patent Number
R-9353
NASA-CR-134387
Accession Number
74N31381
Funding Number(s)
CONTRACT_GRANT: NAS9-12077
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available