Abstract
Abstract : The present trend in liquid rocket engines, gas turbines, and Diesel engines, is towards increasingly higher chamber pressures. In many cases, the chamber pressure can exceed the critical pressures of the fuel or oxidant Above the critical pressure, the distinction between the gas and liquid phases is lost, and mechanisms conventionally associated with subcritical spray combustion no longer necessarily apply. Until recently, relatively little has been understood about the injection and combustion behavior of propellants at supercritical chamber pressures .The results presented here are an extension of our previous work 1,2 systematically investigating liquid rocket injector behavior at subcritical and supercritical pressures.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
