PROPELLANT SPRAYS IN LIQUID ROCKET ENGINES.
Abstract
The research described in this report is directed at obtaining an understanding of the behavior of propellant sprays in a liquid propellant rocket engine under oscillating flow conditions as a means of relating combustion stability to propellant properties and injector design. The report covers: (1) an outline of the work on the instability problem; (2) the combustion instability model; (3) calculation of fluctuations in the vaporization of liquid sprays for axisymmetric injection; (4) preliminary formulation of a transient problem associated with pressure oscillations in a rocket chamber; (5) calculation of Green's function for the transient instability problem; (6) a simple example of the calculation of the spray distribution function and the stability criterion; and (7) perturbation method for calculating stability boundaries. Sections 2 and 3 are related to treating a linear type instability where all oscillations are acoustic in nature. Sec 4 deals with the development of finite amplitude waves. In Sec. 5 a method of solution of the transient instability problem is discussed. Sections 6 and 7 cover a sample calculation of the spray distribution function and stability criterion. Significant results show that droplet vaporization can be a cause of combustion instability and that stability boundaries can be predicted from injector parameters and propellant properties. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1966
- Accession Number
- AD0637236
Entities
People
- Melvin Gerstein