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