Accession Number : ADA329776
Title : Contributions of Atomization, Vaporization and Combustion to Liquid Rocket Acoustic Energy
Descriptive Note : Final technical rept. 1 Jul 94-30 Jun 97
Corporate Author : PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF AEROSPACE ENGINEERING
Personal Author(s) : Micci, Michael M.
PDF Url : ADA329776
Report Date : 15 SEP 1997
Pagination or Media Count : 7
Abstract : Acoustic oscillations were induced in a sub-scale liquid rocket engine that burned liquid oxygen and gaseous hydrogen as propellants. The oscillations in the chamber were forced by a rotating gear just downstream of the nozzle throat. High frequency data was acquired for pressure and velocity via a pressure transducer and a magnetic flowmeter. The magnetic flowmeter obtains the acoustic gas velocity by measuring the voltage induced by the ionized combustion products moving through an externally imposed magnetic field. A cross correlation was performed on the velocity and pressure signals to determine the amplitude and phase difference of the two signals.
Descriptors : *LIQUID PROPELLANT ROCKET ENGINES, *LIQUID PROPELLANTS, *COMBUSTION STABILITY, *VAPORIZATION, *ATOMIZATION, *ROCKET ENGINE NOISE, HIGH FREQUENCY, HYDROGEN, GASES, PRESSURE, ACOUSTICS, OSCILLATION, FLOWMETERS, NOZZLE THROATS, LIQUID OXYGEN.
Subject Categories : Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE