Add to ORKGThe combustion stability characteristics of a combustor consisting of a single shear element and a cylindrical chamber utilizing LOX and gaseous hydrogen as propellants are presented. The combustor geometry and the resulting longitudinal mode instability are axisymmetric. Hydrogen injection temperature and pyrotechnic pulsing were used to determine stability boundaries. Mixture ratio, fuel annulus gap, and LOX post configuration were varied. Performance and stability data are presented for chamber pressures of 300 and 1000 psia
This article explores the possibility of analyzing combustion instabilities in liq- uid rocket engin...
Test firings and analytical model used to evaluate chugging instability in subscale experiments with...
Injector behavior is of utmost importance for the performance and stability of liquid rocket engines...
Test data from NASA Lewis' Effect of Thrust Per Element on Combustion Stability Characteristics of H...
Coaxial injector thrust effects on combustion stability of hydrogen-oxygen rocket engin
Experimental data from a longitudinally unstable uni-element model rocket combustor are analyzed usi...
Determination of combustion stability limits with hydrogen-oxygen combustor of variable lengt
This paper is a compilation of the research efforts of five different groups (Bertin Technologies an...
In 40K methane/LOX 5 KHz engine tests, (first transverse mode) combustion instabilities observed by ...
Liquid oxygen set behavior during combustion instability in gaseous hydrogen fueled rocket combusto
Liquid rocket engines using oxygen and methane propellants are being considered by the National Aero...
Gaseous methane and 90% hydrogen peroxide at an equivalence ratio of 0.8 were used to study combusti...
The overall objective of the current research is to evaluate if and how computational fluid dynamics...
Rocket engines achieve extraordinary high energy densities within the chamber in the form of high pr...
With recent improvements in computer architecture, there are renewed interests in studying combustio...
This article explores the possibility of analyzing combustion instabilities in liq- uid rocket engin...
Test firings and analytical model used to evaluate chugging instability in subscale experiments with...
Injector behavior is of utmost importance for the performance and stability of liquid rocket engines...
Test data from NASA Lewis' Effect of Thrust Per Element on Combustion Stability Characteristics of H...
Coaxial injector thrust effects on combustion stability of hydrogen-oxygen rocket engin
Experimental data from a longitudinally unstable uni-element model rocket combustor are analyzed usi...
Determination of combustion stability limits with hydrogen-oxygen combustor of variable lengt
This paper is a compilation of the research efforts of five different groups (Bertin Technologies an...
In 40K methane/LOX 5 KHz engine tests, (first transverse mode) combustion instabilities observed by ...
Liquid oxygen set behavior during combustion instability in gaseous hydrogen fueled rocket combusto
Liquid rocket engines using oxygen and methane propellants are being considered by the National Aero...
Gaseous methane and 90% hydrogen peroxide at an equivalence ratio of 0.8 were used to study combusti...
The overall objective of the current research is to evaluate if and how computational fluid dynamics...
Rocket engines achieve extraordinary high energy densities within the chamber in the form of high pr...
With recent improvements in computer architecture, there are renewed interests in studying combustio...
This article explores the possibility of analyzing combustion instabilities in liq- uid rocket engin...
Test firings and analytical model used to evaluate chugging instability in subscale experiments with...
Injector behavior is of utmost importance for the performance and stability of liquid rocket engines...