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):

Report Date:

1997-09-15

Pagination or Media Count:

7.0

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.

Subject Categories:

  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE