Accession Number:

AD0258231

Title:

A SPRAY COMBUSTION MODEL WITH DROPLET BREAKUP INCLUDING GAS DYNAMIC COUPLING

Descriptive Note:

Technical Report

Corporate Author:

POLYTECHNIC INST OF BROOKLYN NY BROOKLYN United States

Personal Author(s):

• BURSTEIN,Samuel Z.
• HAMMER,Sanford S.
• AGOSTA,Vito D.

Report Date:

1961-06-01

Pagination or Media Count:

41.0

Abstract:

A simplified model is proposed for the combustion of a bi-propellant spray. The model considers 2 subsystems, the spray, and the combusted gases. These subsystems are coupled together by heat transfer, mass transfer and momentum transfer. The solution of the problem relies upon the integration of a system of 7 nonlinear differential equations. Under the given boundary conditions a co-operative evaporation process occurs, in which increased velocity gradients cause increased evaporation which increases the velocity gradient. Tests were made on a 2-in. diam, variable length rocket motor, using JP-5A and LOX. A simple converging diverging nozzle is employed to give high chamber exit Mach numbers .4 to .5. For a given set of injection parameters, under stable operating conditions, the results indicate that the steepest portion of the gradient, which corresponds to evaporation of the major portion of the fuel, is always found in a fixed region of the chamber, independent of the absolute length of the chamber. Results appear to be in agreement with the theory.

Descriptors:

• COMBUSTION
• DROPS
• FUEL SPRAYS
• LIQUID ROCKET PROPELLANTS
• SPRAYS
• COMBUSTION CHAMBER GASES
• COMBUSTION CHAMBERS
• DIFFUSION
• EVAPORATION
• FLUID MECHANICS
• GAS FLOW
• INJECTION
• INJECTORS
• JET ENGINE FUELS
• LIQUEFIED GASES
• MATHEMATICAL ANALYSIS
• OXYGEN
• ROCKET FUELS
• ROCKET ENGINES
• ROCKET PROPELLANTS
• OXIDIZERS
• VAPORIZATION
• VELOCITY

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE