A SPRAY COMBUSTION MODEL WITH DROPLET BREAKUP INCLUDING GAS DYNAMIC COUPLING

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.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1961
Accession Number
AD0258231

Entities

People

  • Samuel Z. Burstein
  • Sanford S. Hammer
  • Vito D. Agosta

Organizations

  • New York University Tandon School of Engineering

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Combustion
  • Critical Temperature
  • Differential Equations
  • Engineering
  • Fluid Dynamics
  • Heat Energy
  • Heat Transfer
  • Jet Propulsion
  • Latent Heat
  • Mach Number
  • Mechanical Engineering
  • Partial Pressure
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Rocket Engines
  • Vapor Pressure

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Control Systems Engineering.
  • Operations Research