COMBUSTION CHARACTERISTICS OF BI-PHASE ROCKETS,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1970
- Accession Number
- AD0706890
Entities
People
- John R. Osborn
- Richard R. Weiss
Organizations
- Purdue University