Combustion Instability in Liquid Propellant Rocket Engines: Bi-Propellant Spray Combustion
Abstract
A model is proposed for the combustion of a bi-propellant spray in a rocket motor. The model considers evaporation of both fuel and oxidizer without any restrictive assumption concerning their relative rates. A series of steady state and wave propagation experiments are conducted with a 2-inch diameter variable length rocket motor using JP-5A and liquid oxygen. The steady state experiments are primarily concerned with the measurement of axial combustion analysis and provide initial conditions for wave propagation studies. Wave propagation experiments are conducted by utilizing the combustion chamber as a driven tube and mounting a diaphragm and high pressure driver tube upstream of the injector. The results indicate that wave steepening and pressure amplification are strongly coupled to the steady state gas dynamic flow field through which the wave must propagate.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1966
- Accession Number
- AD0487783
Entities
People
- Sanford S. Hammer
- Vito D. Agosta
- William T. Peschke
Organizations
- New York University Tandon School of Engineering