Effect of thrust per element on combustion stability characteristics of hydrogen oxygen rocket engines

The results obtained with a series of 10.78-inch (0.2'7-m) coaxial injectors on a 20 000-pound (88 964-N) thrust oxygen-hydrogen rocket engine operated a t a chamber pressure of 300 psia (2.064 MN/m ) were analyzed to determine the effects of injector thrust per element T/E on the combustion stability.The thrust per element ranged from about 20 to 2500 pounds (88.96 to 11 120 N).Based on the minimum hydrogen temperature for stable combustion, the combustion stability increased with increasing thrust per element.No combustion instability was observed at a thrust per element of 200 pounds (889.6 N) or above.T/E injectors failed to induce combustion instability.tures of the unstable injectors showed agreement with two different correlating parameters.