ENGINEERING METHOD FOR THERMODYNAMIC CALCULATIONS OF JET-TYPE COMBUSTION CHAMBERS USING HYDROCARBON FUEL AND AIR,
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
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A method is presented for determining the temperature and composition of the working substance in a combustion chamber and at the nozzle exit. The method is suitable for any fuel with a C, H, O, and N composition. The working substance coefficient and temperature in the combustion chamber and at the nozzle exit cross-section are found from a set of equations representing the combustion process at constant pressure and isoentropic expansion up to a given pressure at the nozzle exit cross-section.
- Combustion and Ignition