PROPELLANT SPRAYS IN LIQUID ROCKET ENGINES.
Final scientific rept. 1 Apr 65-31 Mar 66.
DYNAMIC SCIENCE CORP MONROVIA CALIF
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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 Greens 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
- Fluid Mechanics
- Combustion and Ignition
- Rocket Engines