Project Title:

Non-Intrusive Measurement of Fuel Droplet Regression Rates in Liquid Rocket Engines Using Morphology Dependent Resonance Scattering

	  94-1	11.01	6688

	  Non-Intrusive Measurement of Fuel Droplet Regression Rates in 
	  Liquid Rocket Engines Using Morphology Dependent Resonance 
	  Scattering

Abstract:

The development of efficient liquid rocket engines depends to 
some extent on our ability to develop realistic and reliable 
theoretical spray combustion models that can accurately predict 
its performance characteristics. To-date, several spray 
combustion models have been developed. But many of these make 
questionable assumptions with regard to the complex physical, 
chemical, and fluid-mechanical processes that occur in a reactive 
spray environment. One questionable assumption pertains to the 
burning/evaporation rate of droplets in a reactive spray. This 
proposal deals with the development of an innovative laser-based 
technique for the non-intrusive measurement of fuel droplet 
regression rates in reactive sprays. The measurement technique 
is based on the resonance elastic light scattering 
characteristics (resonance spectroscopy) of spherical particles. 
This research program will examine the feasibility of developing 
such a measurement technique and integrating it with the phase 
Doppler particle analyzer and the rainbow thermometer to yield 
an instrument that can be used for the simultaneous measurement 
of droplet size, velocity, temperature, and instantaneous 
regression rates of individual fuel droplets in complex reactive 
sprays.

The successful completion of the Phase I and Phase II program 
will yield a novel diagnostic instrument that can be used to 
develop and validate theoretical spray combustion models, and to 
obtain a better understanding of the complex spray combustion 
process. Hence, such an instrument is bound to have significant 
commercialization potential.

Key Words

Aerometrics, Inc.
550 Del Rey Avenue
Sunnyvale, CA 94086