Nonlinear longitudinal combustion instability in rocket motors.A new analytical technique for the solution of nonlinear longitudinal combustion instability problems in rocket combustors is developed. Using relatively little computation time, this technique is capable of predicting the transient and limit cycle behavior of the combustion instability oscillations as well as the disturbance amplitude required to trigger an instability in a linearly stable motor. The limit cycle waveforms are found to exhibit shock wave characteristics for most unstable engine operating conditions. It is shown that the characteristics of the resulting instability are independent of the nature of the initial disturbance and they depend solely upon the engine operating conditions and the characteristics of the unsteady combustion process.
Document ID
19730032145
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lores, M. E. (Vought Aeronautics Co. Dallas, Tex., United States)
Zinn, B. T. (Georgia Institute of Technology Atlanta, Ga., United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1973
Subject Category
Thermodynamics And Combustion
Report/Patent Number
AIAA PAPER 73-217
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Washington, DC
Start Date: January 10, 1973
End Date: January 12, 1973
Sponsors: American Institute of Aeronautics and Astronautics