The development is discussed of analytical techniques and numerical methods for the prediction of the stability behavior of liquid propellant rocket combustors with partial length acoustic liners, injector face baffles, and nonlinear combustion responses. Three primary objectives included: (1) extension of the Green's Function integral-iteration technique previously developed so that nonlinear three dimensional wave propagation effects could be included in stability predictions; (2) development of an analytical technique and a computer program for the prediction of the damping effects caused by injector face baffles; and (3) inclusion of a nonlinear, wave distortation dependent, combustion response model in the global stability analysis and...
Stabilizing influence of acoustic cavities on acoustic modes of combustion instability in rocket eng...
A technique for predicting the stability characteristics of a gaseous-propellant rocket combustion s...
The theory and procedures for determining the characteristics of pressure oscillations in rocket eng...
Analytical and computational techniques were developed to predict the stability behavior of liquid p...
An analytical model is formulated for a three-dimensional nonlinear stability problem in a rocket mo...
An analytical technique for the evaluation of combustion stability in rocket motors with partial len...
Analytical studies have been made of the relative combustion stability of various propellant combina...
A program for predicting the linear stability of liquid propellant rocket engines is presented. The ...
The problems of combustion instability in an annular combustion chamber are investigated. A modified...
An analytical technique was developed to solve nonlinear longitudinal combustion instability problem...
Small amplitude linear analysis of combustion instability with finite Mach number flow and acoustic ...
Nonsteady flow conditions in subsonic section of Laval nozzle to investigate nonlinear transverse co...
Approximate models for amplification by wave distortion of dynamic response of vaporization limited ...
The theory and procedures for determining the characteristics of pressure oscillations in rocket eng...
The development of an analytical technique used in the solution of nonlinear velocity-sensitive comb...
Stabilizing influence of acoustic cavities on acoustic modes of combustion instability in rocket eng...
A technique for predicting the stability characteristics of a gaseous-propellant rocket combustion s...
The theory and procedures for determining the characteristics of pressure oscillations in rocket eng...
Analytical and computational techniques were developed to predict the stability behavior of liquid p...
An analytical model is formulated for a three-dimensional nonlinear stability problem in a rocket mo...
An analytical technique for the evaluation of combustion stability in rocket motors with partial len...
Analytical studies have been made of the relative combustion stability of various propellant combina...
A program for predicting the linear stability of liquid propellant rocket engines is presented. The ...
The problems of combustion instability in an annular combustion chamber are investigated. A modified...
An analytical technique was developed to solve nonlinear longitudinal combustion instability problem...
Small amplitude linear analysis of combustion instability with finite Mach number flow and acoustic ...
Nonsteady flow conditions in subsonic section of Laval nozzle to investigate nonlinear transverse co...
Approximate models for amplification by wave distortion of dynamic response of vaporization limited ...
The theory and procedures for determining the characteristics of pressure oscillations in rocket eng...
The development of an analytical technique used in the solution of nonlinear velocity-sensitive comb...
Stabilizing influence of acoustic cavities on acoustic modes of combustion instability in rocket eng...
A technique for predicting the stability characteristics of a gaseous-propellant rocket combustion s...
The theory and procedures for determining the characteristics of pressure oscillations in rocket eng...