The Determination of the Laval Nozzle Exit Conditions at a Too High Counter-Pressure Especially for a Propane Oxygen Gas Generator

摘要

The flow conditions in a supersonic nozzle including normal shock were investigated. A more dimensional calculation method for an ideal gas is presented to compute the nozzle exit parameters and the location of the shock. The boundaries of the pressure behind the nozzle were calculated. For gas from the combustion of propane and oxygen, it is shown that the consequences of real gas effects on the results of the method are small. Experimental measurements on nozzles with air flow show the validity of the method. At a propane oxygen gas generator, the exhaust temperature is very high; therefore, measurements are possible only in the jet behind the nozzle exit. The pilot pressure and the temperature measurements show that the chemical reaction in the combustion chamber was incomplete.