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