ANALYSIS OF LIQUID ROCKET ENGINE COMBUSTION INSTABILITY
Abstract
This report develops a nonlinear model which can be used to predict combustion instability zones in liquid rocket engines. The model is developed by combining a nonlinear instability model with a steady-state vaporization model. Such an analysis determines the zones of an engine in which a tangential mode of high frequency instability is most easily initiated. A rocket engine can be analyzed by incrementally dividing the combustion chamber into annular nodes in the r and z directions. Steady-state properties at each annular node or position in the chamber are computed from the steady-state vaporization computer program. The steady-state program is capable of computing combustion profiles in thermally unstable propellants of the monomethylhydrazine/nitrogen tetroxide type. This model describes droplet vaporization with vapor phase decomposition. Using the computed steady-state properties and the stability limit curves from the instability computer program, stability at each node is determined. This process is repeated for each node to determine a stability map of the entire engine.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1966
- Accession Number
- AD0482021
Entities
People
- B. P. Breen
- C. F. Sanders
- M. R. Beltran
- R. J. Hoffman
- T. C. Kosvic