Accession Number : AD0706890

Title :   COMBUSTION CHARACTERISTICS OF BI-PHASE ROCKETS,

Corporate Author : PURDUE UNIV LAFAYETTE IND SCHOOL OF MECHANICAL ENGINEERING

Personal Author(s) : Weiss,Richard R. ; Osborn,John R.

Report Date : MAY 1970

Pagination or Media Count : 150

Abstract : The report describes an experimental and analytical investigation conducted for evaluating the influence of combustion chamber pressure and propellant temperature effects on liquid rocket combustion dynamics. The experimental program was conducted with a small-scale rocket engine thrust chamber assembly using bi-phase propellants. Air was used as the oxidizer and normal heptane was used as the fuel. Chamber pressures investigated ranged from 250 to 1000 psia; values below the critical pressure of the fuel to ones considerably above it. The values for the initial temperature of the injected fuel ranged from 520 degrees R to 910 degrees R. It was found that increasing the chamber pressure has a strong stabilizing effect, increasing the initial fuel temperature has a slight destabilizing effect and decreasing the drop size has strong destabilizing effect. Two combustion models were used for obtaining analytical predictions of the stability behavior for correlating the experimental results and the the determining the validity of the models. (Author)

Descriptors :   (*HYBRID ROCKET ENGINES, PERFORMANCE(ENGINEERING)), (*HYBRID ROCKET PROPELLANTS, COMBUSTION), DROPS, VAPORIZATION, BURNING RATE, BIPROPELLANTS, INJECTORS, STABILITY, PRESSURE, EXPERIMENTAL DATA, LIQUID ROCKET FUELS

Subject Categories : Combustion and Ignition
      Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE