Accession Number : ADA329657

Title :   Fundamental of Acoustic Instabilities in Liquid-Propellant Rockets

Descriptive Note : Final rept.

Corporate Author : CALIFORNIA UNIV SAN DIEGO LA JOLLA

Personal Author(s) : Williams, F. A.

PDF Url : ADA329657

Report Date : 14 APR 1997

Pagination or Media Count : 7

Abstract : The objective of this research was to improve understanding of the mechanisms by which flow, mixing and combustion processes are coupled to acoustic fields in liquid propellant rocket motors. Particular attention was focused on analyses of amplification mechanisms coupled with finite rate chemical reactions by use of numerical and analytical methods. A theoretical explanation of empirical correlation of instability boundaries for engine test results for LOX/RP-1 rockets was developed on the basis of amplification by finite rate chemical reactions in strained mixing layers. In addition, a new numerical computation of nonlinear amplification mechanisms in LOX/GH2 combustion suggested a possible explanation of threshold phenomena found in liquid propellant rockets.

Descriptors :   *ACOUSTIC WAVES, *LIQUID PROPELLANT ROCKET ENGINES, *COMBUSTION STABILITY, TURBULENCE, STRAIN RATE, COMBUSTION CHAMBERS, LIQUID PROPELLANTS, ACOUSTIC FIELDS, HEAT OF COMBUSTION, EXHAUST FLAMES.

Subject Categories : Liquid Propellant Rocket Engines
      Acoustics

Distribution Statement : APPROVED FOR PUBLIC RELEASE